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SRAAM
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SRAAM
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The Short Range Air-to-Air Missile (Short-Range Anti-Air Missile in NATO AAP-15), or SRAAM for short, initially known as Taildog, was an experimental British infrared homing ("heat seeking") air-to-air missile, developed between 1968 and 1980 by Hawker Siddeley Dynamics. It was designed to be very manoeuvrable for use at short range in a dogfight situation. The SRAAM was unusual in that it was launched from a launch tube instead of being attached to a launch rail, allowing two to be carried on a single mounting point.

Key Information

Although initially intended to replace the AIM-9 Sidewinder, it was downgraded to a technology demonstrator program in 1974. Between 1974 and 1977, several SRAAM missiles were launched in tests. In 1980, the knowledge gained from the SRAAM project was used in the ASRAAM missile project.

History

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Background

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Early infrared homing missiles had two limitations that made them difficult to use in combat situations. The first was that the seeker was relatively insensitive and required large, hot sources to reliably track a target. In practice, this meant the engine of the enemy aircraft had to remain visible to the missile through the shot. The other was that the seeker had a limited field of view (FOV), meaning it could only see the target if it was in front of the missile. This meant it was possible for the target to escape by flying at right angles to the missile, maximizing its angular velocity relative to the seeker.

These limitations were made clear during the Vietnam War, when early missiles like the AIM-4 Falcon and AIM-9 Sidewinder had success rates on the order of 9% and 14%, respectively. Much of this was due to the fact that pilots had been trained to approach using radar or ground-controlled interception, which placed the enemy aircraft somewhere in front of them, but not necessarily flying in the same direction. In these situations, the seeker might see the target's engine and send the growling signal that indicated lock-on, but would fail to track when fired because the target would move out of the FOV in the time while the missile was flying off the mounting rail.

Faced with these dismal results, the US Navy and then US Air Force introduced new training syllabuses that placed much more emphasis on pre-shot maneuvering, so the launch aircraft would be both behind the target and flying in the same general direction. This would maximize the chance that the target would still be visible to the missile after it was launched. Unfortunately, such maneuvering was both time consuming and potentially difficult to arrange, and in combat there were many situations where a target would cross in front of the fighter in a "snap shot". To provide some capability in these situations, autocannons were hastily added to those fighters that lacked them.

Taildog

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Considering this problem, designers at Hawker Siddeley Dynamics, Hawker's missile division, decided that it would be better to have a missile work like the pilots wanted rather than the pilots working the way the missile wanted. They began designing a missile that would track successfully in every situation where the missile indicated lock-on. In order for this to happen, it would have to have a very wide FOV, or "off-boresight capability", so it would continue to see the target even if it was crossing rapidly. It would also have to have extremely high manoeuvrability so it could successfully track down an aircraft in these situations.

The company began low-level development of such a weapon as a private venture under the name "Taildog" in 1968.[1] This goal was a short-range, low-cost missile that would fill the gap between guns and then-current missiles like the Firestreak and the Red Top. Hawker described it as 'a gun that fires around corners'.[2] The initial design was 2.0 m long, had a diameter of 16.5 cm and weighed 50 kg. It was capable of engaging targets between 250 m and 2 km,[3] as compared to perhaps 12 km under the best case for the Red Top. The first photographs of mock-ups were shown in early 1970,[4] and were displayed at a trade show in Hannover later that year.[5]

The Taildog was highly manoeuvrable through the use of thrust vectoring for all flight control. Vectoring was accomplished by rotating small vanes into the rocket exhaust. Six of these vanes were arranged as segments of a circle at the tail end of the missile body, where they were protected from the rocket exhaust. Each segment was pivoted at one end, allowing it to be rotated so the other end would be moved into the exhaust. The control system would activate the segment closest to the required change in direction. External aerodynamic surfaces were reduced to vestigial surfaces near the rear of the missile, and were unmovable.[6]

Hawker was not the only one to come up with this basic concept; around the same time, the US Navy and the Air Force both began similar programs for similar reasons, ultimately combining their efforts in the AIM-95 Agile project. The Taildog and the Agile differed primarily in range; the Taildog was intended as a short-range dogfighting weapon, while the Agile was a replacement for the Sidewinder and set range requirements at least as good as that missile, producing a much larger design.

SRAAM

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In 1970 the British Ministry of Defence came to the conclusion that a better short-range missile was needed, and drew up a request for proposals, AST 1218.[3] AST 1218 also included the requirement that the missile could be carried by aircraft that lacked the radar-aided target acquisition systems of the Phantom and Lightning.[3]

The Taildog became Hawker Siddeley's response to AST 1218, which became ASR 1222 when the contract was awarded.[3] Hawker's proposal was received favourably, and in 1972 the Ministry of Defence awarded a development contract (Air Staff Requirement 1222). Two versions were studied, the advanced SRAAM-100 and a basic version called SRAAM-75. Both used the same airframe but different electronic fits.[6] The SRAAM was slightly longer than the Taildog, with a length of 2.75 m (9 ft 0 in). The diameter remained the same. The thrust director system was replaced with a moving dome deflector, which consists of a cone-shaped deflector placed in the exhaust which is moved to the sides to cause the thrust to change. The fins were moved to the rear and were reshaped.[7]

The SRAAM was designed to be carried in a launch tube to protect the missile. The fins on the missile were hinged and designed to extend following launch. The launcher comprised two tubes and an optional radar cueing system, enabling the missile to be carried by almost any aircraft with little modification. The missile could be fired automatically when a target came into view of the seeker,[8] unlike, for example, the Firestreak, which needed to be fed targeting information by the aircraft's radar.[9]

SRAAM launcher at Bristol Aero Collection

The contract was cancelled in 1974 due to defence cuts in favour of work on the Skyflash,[10] but retained as a technology demonstration program. In 1977, eight test missiles were fired from the ground and from a Hawker Hunter F.6 (RAF serial XG210).[6] The trials were successful, with one famous incident demonstrating the missile's manoeuvrability when it turned into the Hunter's flight path immediately after launch and almost collided with it.[11] In the same year, the British MOD chose the AIM-9L Sidewinder as its next short-range missile, but the SRAAM project was kept alive to provide a base for a future missile design.[8]

In 1980, the SRAAM work became the starting point for the ASRAAM.[11]

Surviving artefacts include a mockup of the missile in the Royal Air Force Museum Cosford,[12] and a launcher at the Bristol Aero Collection.

See also

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References

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SRAAM

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from Grokipedia
The Short Range Air-to-Air Missile (SRAAM) was an experimental British air-to-air missile developed by Dynamics (later ) primarily for close-quarters aerial combat. Intended as a third-generation short-range weapon system to succeed earlier missiles like the , it incorporated innovative thrust vector control (TVC) for exceptional maneuverability without traditional aerodynamic fins. The project originated from lessons learned during the , emphasizing the need for rapid, visually aimed engagements with positive target identification prior to launch. Development of SRAAM began in the late under the initial codename "Taildog," evolving from earlier into high-agility technologies. By 1970, an advanced design was proposed, but high costs led to a redesign, with the first test firing occurring in April 1977 from a aircraft. The measured 2.724 meters in length and 165 mm in diameter, achieving speeds up to Mach 3, and featured a 90-degree off-boresight capability for firing at targets outside the aircraft's forward view. Its passive seeker allowed for automatic lock-on and launch, with the system designed for instant availability in combat scenarios. Key innovations included a lightweight twin-tube launcher for low drag and the first use of TVC in a rocket motor for air-launched applications, enabling tight turns and high-g maneuvers. Renamed "" in 1973 amid budget constraints, the program was scaled back to a demonstrator by 1974 and ultimately cancelled in 1977, as the Royal Air Force selected the more affordable AIM-9L Sidewinder instead. Despite its termination, SRAAM's technologies influenced subsequent missile designs, such as elements seen in the later . A is preserved at the Midlands as part of the National Exhibition.

Development History

Origins and Requirements

The development of the Short Range Air-to-Air Missile (SRAAM), initially known as Taildog, originated in the late 1960s as a response to lessons learned from the Vietnam War, where U.S. forces identified the need for highly agile short-range air-to-air weapons that could be visually identified and engaged without relying on radar lock-on prior to launch. Hawker Siddeley Dynamics initiated the Taildog study to address the limitations of existing missiles like the AIM-9 Sidewinder, which struggled against rapidly maneuvering targets in close-quarters dogfights. This effort was part of broader British efforts to enhance Royal Air Force (RAF) close-combat capabilities, building on research under contract QC.434 focused on thrust vector control (TVC) technologies for improved missile agility. By 1972, the project had evolved into SRAAM following a formal project definition contract awarded to under Air Staff Requirement (ASR) 1222, with the goal of entering RAF service by 1975. The program's requirements emphasized a , low-drag suitable for visual-range engagements, featuring passive for "fire-and-forget" operation after visual aiming by the pilot. Key specifications included a length of 2.724 meters, a diameter of 165 mm, and a top speed of Mach 3, designed to provide high off-boresight capability and rapid response against both subsonic and supersonic threats. The was required to integrate with a simple tube launcher requiring minimal external connections, enabling compatibility with a wide range of RAF , including those without advanced systems like the Phantom or . These requirements reflected a push for near-instantaneous firing—achieved through automatic launch upon seeker lock-on—using 1970s-era seeker technology to ensure positive target identification in visual range, thereby reducing risks and enhancing pilot survivability in beyond-visual-range transitions to close combat. The design prioritized agility via TVC nozzles over traditional aerodynamic controls, allowing the missile to track highly evasive targets effectively. However, escalating costs in 1974, following the Defence White Paper, led to scope reductions, transforming the program into a technology demonstrator rather than a full production weapon, with formal cancellation in April 1977 in favor of adopting the AIM-9L Sidewinder.

Taildog Program

The Taildog program, initiated by Hawker Siddeley Dynamics in the late 1960s, represented an early British effort to develop a highly maneuverable short-range air-to-air missile capable of countering agile enemy fighters, drawing inspiration from U.S. experiences in the Vietnam War that exposed limitations in existing missile designs. As a private venture project designated QC.434, it focused on thrust vector control (TVC) as the primary steering mechanism, using pivoting nozzles or semaphores to direct exhaust for rapid maneuvers without relying on traditional aerodynamic control surfaces like fins. This innovative approach aimed to enable off-boresight targeting up to 90 degrees and enhance close-combat effectiveness in visual-range engagements, positioning Taildog as a potential successor to older missiles like the Red Top. By 1970, the program had progressed to the point where a Taildog prototype was publicly displayed at a trade exhibition in Hannover, Germany, showcasing its compact design measuring approximately 2.72 meters in length and 165 millimeters in diameter. In 1972, the UK Ministry of Defence provided funding under Air Staff Requirement 1222 to support further development, leading to its evolution into the formal Short Range Air-to-Air Missile (SRAAM) initiative. Renamed Mongoose in 1973, the missile incorporated a solid-fuel rocket motor supplied by Imperial Metal Industries (IMI) Summerfield, achieving speeds up to Mach 3, and was paired with a lightweight twin-tube canister launcher for low-drag, rear-ejection deployment from aircraft. The guidance system relied on passive infrared homing, emphasizing simplicity and cost-effectiveness to fill the gap between guns and longer-range weapons in dogfight scenarios. Testing commenced with over 40 static motor firings at the range in by 1973, validating the TVC system's performance. Initial airborne trials (non-firing) followed in 1975 using a modified aircraft. Despite these successes, the program faced setbacks from 1974 defense budget cuts amid shifting priorities, including the adoption of the U.S. AIM-9L Sidewinder by the RAF in 1977, leading to Taildog's downgrade to a technology demonstrator rather than full production. Its thrust-vectoring innovations and off-boresight concepts nonetheless influenced subsequent British missile efforts, including the AIM-132 .

SRAAM Phase

The SRAAM Phase of the program began in 1972 as an evolution of the earlier Taildog project, transitioning from a private venture by Dynamics to a Ministry of Defence-funded initiative under the official SRAAM designation and Air Staff Requirement 1222. Initially labeled SRAAM-100, the project aimed to deliver a highly maneuverable, third-generation for close-combat engagements, emphasizing thrust vector control (TVC) as the primary steering mechanism to enable rapid response in dogfights. That year, the design was scaled down to SRAAM-75 to reduce costs and complexity for a 1975 in-service date, incorporating a passive seeker for targeting and a solid rocket motor without traditional aerodynamic control surfaces. Key technological advancements during this phase included the adoption of TVC via jet tabs or movable dome deflectors in the exhaust , allowing for 90-degree off-boresight acquisition and extreme agility at speeds up to Mach 3. The missile measured approximately 2.72 meters in length and 0.165 meters in diameter, with a lightweight twin-tube launcher featuring retractable nose doors to minimize drag on like the . Propulsion was provided by a solid rocket motor developed by Imperial Metal Industries (IMI) Summerfield, while control actuation systems came from Sperry , enabling the missile to function as a "fire-and-forget" weapon once the seeker locked on. These innovations positioned SRAAM as a pioneer in thrust-vectoring technology for short-range s, addressing limitations of earlier designs like the in high-maneuverability scenarios informed by experiences. Development progressed through extensive ground testing starting in 1973 at the range, where over 40 motor firings validated the TVC system and structural integrity. Initial airborne trials occurred in 1975 using a modified aircraft, with the first guided test firing in April 1977 and approximately eight guided launches completed between 1977 and program end that successfully demonstrated the missile's ability to track and intercept targets with high precision, including one instance of near-boomerang maneuverability. However, the 1974 UK Defence White Paper imposed severe budget cuts, relegating SRAAM to a demonstrator status and halting full-scale production efforts. In 1977, the program was formally cancelled in favor of procuring the off-the-shelf AIM-9L Sidewinder, which offered quicker availability and lower costs despite SRAAM's superior performance potential. Its thrust-vectoring and seeker technologies directly informed the subsequent (ASRAAM) program starting in 1980. Artifacts from the SRAAM Phase, including mockups and launchers, are preserved at the RAF Museum (Cosford), underscoring its role as a foundational effort in missile innovation.

Design and Technology

Guidance and Seeker

The Short Range (SRAAM) utilized a passive (IR) homing guidance system, enabling heat-seeking acquisition of targets without active emission. This system was visually aimed by the pilot, with the missile's forward compartment housing the IR seeker alongside the safety-actuating mechanism, , and electronics. The seeker's design supported an off-boresight capability of 90 degrees, allowing launches from extreme angles relative to the aircraft's nose, which enhanced close-range combat flexibility in scenarios. Steering was provided exclusively by thrust vector control (TVC), eliminating the need for aerodynamic fins or control surfaces. The TVC system employed electrically operated semaphores to deflect the exhaust plume by up to 18 degrees using jet tabs at the exhaust nozzle, enabling rapid maneuvers throughout the missile's . This integration of the IR seeker with TVC represented an innovative approach for short-range missiles of the era, prioritizing high agility and minimal drag in a tube-launched configuration.

Propulsion and Aerodynamics

The SRAAM employed a single-stage motor developed by IMI Summerfield, providing propulsion for high-speed, short-range engagements. This motor was integrated into a compact design, with the achieving a top speed of Mach 3. vector control (TVC) was a pioneering feature of the SRAAM, marking it as the first air-launched worldwide to incorporate this technology for enhanced maneuverability. The system utilized electrically actuated semaphores, or jet tabs, positioned at the exhaust to deflect the plume by up to 18 degrees without incurring losses during neutral operation. Over 100 motor static tests were conducted, including approximately 40 that demonstrated TVC functionality, validating the system's reliability under operational conditions. Aerodynamically, the SRAAM featured a wingless, tube-launched configuration with a of 2.724 and a of 165 , minimizing drag during carriage and enabling rapid deployment from . Lacking traditional control surfaces, the relied on body lift from its cylindrical for primary aerodynamic forces, supplemented by six sprung fins mounted on a rotating stabilization ring that deployed after launch. This spin-stabilized design, combined with low-drag launch tubes featuring retractable nose doors, supported off-boresight firing angles of up to 90 degrees and high-g maneuvers essential for close-range dogfights.

Warhead and Launch Configuration

The SRAAM featured a high-explosive detonated by either a proximity or impact fuse. This configuration emphasized reliability and simplicity, aligning with the missile's role as a lightweight, cost-effective weapon intended to complement longer-range systems. The launch setup utilized a compact, underwing twin-tube launcher that accommodated two missiles side-by-side within protective tubes, integrated with onboard fire control equipment for streamlined operation. The design incorporated low-drag features, including nose doors on the tubes that opened during firing and closed afterward to reduce aerodynamic penalties on the host aircraft. This tube-based approach, rather than traditional rails, protected the missile's folding fins—which deployed post-launch—and enabled thrust vector control via semaphores for high maneuverability immediately after egress. The launcher's modular nature facilitated broad compatibility, requiring little to no structural or modifications for integration on interceptors, fighters, or platforms, such as the during testing. It supported visually aimed firing with passive guidance, including an off-boresight acquisition angle of up to 90 degrees, allowing pilots to engage targets without precise alignment. This emphasis on simplicity and rapid response made the SRAAM suitable for lacking advanced targeting systems, enhancing its tactical flexibility in beyond-visual-range transitions to dogfights.

Testing and Performance

Ground and Early Trials

Ground testing of the Short Range Air-to-Air Missile (SRAAM) began in 1973 at the test range in , following the project's definition phase initiated in under a contract awarded to Dynamics. These initial trials focused on validating the missile's solid-propellant motor, supplied by Imperial Metal Industries (IMI), and its innovative thrust vector control system using jet tabs. The tests involved multiple ground launches, demonstrating the propulsion system's ability to achieve precise control without traditional aerodynamic surfaces. Over 100 motor firings were performed in various configurations during this period, with approximately 40 conducted in the definitive form by late 1973. Roughly half of these definitive firings incorporated jet tab operation to simulate under operational conditions, confirming the system's reliability and responsiveness. The ground trials successfully passed milestones, establishing a foundation for the missile's all-aspect seeker and high-agility design, though the program was soon impacted by broader defense reductions. Early flight trials followed in 1975, marking the transition from static testing to airborne demonstrations. A small number of launches were carried out from a aircraft, serving primarily as a technology demonstrator after the 1974 Defence White Paper downgraded SRAAM from a full production program. These tests verified basic and seeker in a dynamic environment, with plans for additional launches in 1976 to further assess integration and control. A subsequent test firing occurred in April 1977, highlighting the missile's potential for rapid and high off-boresight capability.

Flight Test Results

The flight tests of the Short Range Air-to-Air Missile (SRAAM) were conducted as part of its development as an experimental infrared-homing weapon, focusing on validating its thrust-vectoring propulsion, , and high-maneuverability in close-range engagements. A small number of airborne launches took place in 1975 from a aircraft, demonstrating promising performance in terms of control and under dynamic flight conditions. Further trials in 1977 included a test firing from a aircraft, confirming the missile's seeker capabilities. The trials overall were successful, achieving direct hits and validating the design's agility at speeds up to Mach 3, though quantitative metrics such as hit probabilities were not publicly detailed due to the program's classified aspects. A test firing occurred in April 1977, demonstrating the seeker's capabilities. These results underscored the innovative use of thrust vector control for enhanced off-boresight firing, but budget constraints limited further evaluations, leading to the program's downgrade to a technology demonstrator.

Evaluation and Challenges

The SRAAM program underwent rigorous ground and that validated its innovative features, particularly its thrust-vectoring system, which enabled exceptional maneuverability and a 90-degree off-boresight firing capability. Initial ground trials at the range in 1973 successfully demonstrated the missile's infrared seeker and low-drag canister launch mechanism. Subsequent flight tests from a aircraft in 1975 confirmed high-speed performance, reaching Mach 3, and reliable target acquisition in visual-range engagements. A live-fire test in April 1977 further affirmed the missile's effectiveness and overall agility, positioning it as a potential superior replacement for the in close-combat scenarios. Despite these positive results, the program encountered substantial challenges, primarily driven by escalating development costs and budgetary constraints. The original 1970 design was deemed overly expensive, prompting a 1974 redesign to simplify components and reduce expenses, though this delayed progress. The 1974 UK Defence White Paper imposed severe funding cuts, downgrading SRAAM from a full operational to a technology demonstrator, limiting further full-scale development. Competition from established alternatives, such as the French Matra and the US AIM-9L Sidewinder, intensified pressures, as the latter offered proven reliability at lower acquisition costs. These factors culminated in the 1977 decision to select the AIM-9L for RAF service, effectively halting SRAAM's path to production despite its technical promise. The program's challenges highlighted broader tensions in defence policy between innovation and fiscal prudence during a period of economic strain.

Cancellation and Legacy

Factors Leading to Cancellation

The SRAAM program faced significant challenges due to escalating defense budget constraints in the early . The British government's 1974 Defence White Paper, issued under the newly elected Labour administration, mandated substantial reductions in expenditure to address economic pressures, including high and a balance-of-payments crisis. As a result, the full-scale development contract for SRAAM, awarded to Dynamics in 1970, was cancelled, with the project downgraded to a effort. This decision saved less than £10 million but reflected broader cuts that prioritized immediate operational needs over innovative domestic projects. A key factor in the cancellation was the availability of more cost-effective and readily deployable alternatives from international partners. The Royal Air Force (RAF) and required an urgent upgrade to short-range capabilities, and foreign options like the American AIM-9L Sidewinder and the French Matra offered proven performance without the risks and delays of SRAAM's advanced features, such as thrust-vectoring control and all-aspect . In April 1977, the RAF formally selected the AIM-9L for its , citing the missile's immediate availability in large quantities during potential emergencies, which aligned with post-Yom Kippur War assessments of rapid procurement needs. Additionally, SRAAM's ambitious design—intended for a 1976 in-service date—proved overly complex given the technological limitations of the era, particularly that constrained further enhancements. The program's high development costs clashed with fiscal measures that favored off-the-shelf solutions over systems. These elements collectively shifted priorities toward with allies and deferred advanced domestic missile development until the 1980s program.

Technological Influence and Successors

Despite its cancellation in 1977, the SRAAM project exerted considerable influence on subsequent short-range designs through its innovative engineering solutions. The missile's reliance on thrust vector control (TVC) as the exclusive steering mechanism—without aerodynamic fins—enabled unprecedented agility, with demonstrated maneuverability exceeding that of contemporary rivals like the U.S. , contributing to the latter's termination. This approach minimized drag and allowed for instantaneous post-launch turns, addressing limitations in close-quarters dogfighting observed during the . The SRAAM's passive infrared seeker, capable of all-aspect targeting and wide-angle acquisition, further advanced capabilities, reducing pilot workload in dynamic engagements. The project's technologies directly informed the development of the Advanced Short Range Air-to-Air Missile (, or AIM-132), which emerged as its primary successor. Initiated in the early 1980s as a collaborative effort involving the , , , and to counter advanced Soviet threats like the R-73, the ASRAAM program built on SRAAM's foundational technologies and research, incorporating refined TVC for enhanced end-game maneuverability (up to 50g) alongside aerodynamic controls for stability. The ASRAAM retained the emphasis on high supersonic speeds (over Mach 3), extended effective range for its class (beyond 20 km), and an advanced seeker supporting lock-on after launch, enabling pilots to evade counterfire immediately after missile release. After the international partnership dissolved in 1990, the proceeded independently, with (formerly ) leading production; the missile achieved initial operational capability with the Royal Air Force in 2002. As of 2025, ASRAAM has achieved full integration with the F-35 Lightning II and continues to be employed in ground-based air defense roles in . SRAAM's tube-launched, low-drag container design also influenced modular launch systems in modern missiles, allowing carriage of multiple rounds without compromising aircraft aerodynamics—a feature evident in 's integration on platforms such as the , F-35 Lightning II, and . This legacy extended to broader within-visual-range missile paradigms, prioritizing agility and over size and cost, and informed non-U.S. programs like the German , which adopted similar TVC elements for superior off-boresight performance. ASRAAM itself has seen upgrades, including helmet-cued targeting and surface-launched variants, perpetuating SRAAM's emphasis on versatile, high-impact short-range lethality.
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