S-24 rocket
The S-24 rocket is a 240 mm unguided air-to-surface rocket developed by the Soviet Union, featuring a solid-propellant motor and a high-explosive fragmentation warhead for engaging armored vehicles, fortifications, and troop concentrations from aircraft and helicopters.[1] Weighing 235 kg with a length of 2.33 m, it achieves a maximum speed of 410–430 m/s and an effective range of 2–3 km when launched from low altitudes.[2] Development took place in the 1950s by the NII-1 design bureau, with state trials conducted in 1958, leading to entry into service in 1964.[1][2] Introduced as part of the Soviet Air Force's effort to enhance close air support capabilities during the Cold War, the S-24 succeeded earlier World War II-era rockets like the BETAB-750DS and was produced in large quantities from the early 1960s onward.[3] Its 123 kg warhead contains 25.5 kg of explosive, generating up to 4,000 fragments with a lethal radius of 300–400 m and the ability to penetrate 25–30 mm of armor or 1 m of reinforced concrete, depending on the fuse type.[1][2] The rocket is stabilized by fixed cranked fins and spin (450–470 rpm) imparted by its seven-nozzle solid-fuel motor, ensuring accuracy with a deviation of 0.3–0.4% of the flight range.[3][1] Variants include the baseline S-24 with an impact fuse for direct hits, the S-24B with low-smoke propellant (and a configuration using delayed-action fuse for bunker-busting), and the S-24N equipped with a proximity fuse for airburst effects up to 30 m altitude.[1] These are launched from rails such as the early PU-12-40U or later APU-7D and APU-68U pods, compatible with aircraft like the Su-7, MiG-21, MiG-23, Su-25, and helicopters including the Mi-24.[2] Originally designated 9A-357 (S-24) and 9A-744 (S-24B), it remains in service with the Russian Aerospace Forces and has been exported or license-produced, such as Iran's Shafagh variant.[1][4] The S-24's design emphasized simplicity, power, and reliability, making it a staple in Soviet and post-Soviet ground-attack operations despite the rise of precision-guided munitions.[2]History
Development
The S-24 rocket emerged in the post-World War II era as part of the Soviet Union's efforts to advance unguided air-to-ground munitions, succeeding earlier designs like the BETAB-750DS to enhance destructive capabilities against armored and infantry targets. Development began in the 1950s, driven by the need to overcome range and power limitations in prior 132 mm and 80 mm rockets, with the goal of creating a more potent 240 mm weapon for tactical aviation roles.[5] The project was led by the NII-1 design bureau under the Soviet Ministry of Aviation Industry, involving collaborative work among aviation research institutes to modernize the unguided rocket family that included smaller systems like the S-5 series. Initial prototypes underwent ground testing for propulsion and structural integrity in the mid-1950s, followed by aerial integration trials with early jet fighters to evaluate launch stability and trajectory accuracy. Key milestones included state trials conducted in 1958, which identified and addressed issues in rocket stabilization and motor performance through iterative refinements. These phases culminated in the rocket's validation for operational use around 1960, solidifying its role in Soviet air force modernization.Production and service entry
Mass production of the S-24 rocket began in the early 1960s at Soviet state factories, following successful state trials in 1958.[1] The rocket was officially adopted into service with the Soviet Air Force in 1964, becoming a standard unguided air-to-surface weapon integrated into aircraft armament systems.[1][2] An improved variant, the S-24B with a smokeless solid-propellant motor, entered production and service in the mid-1970s, enhancing operational stealth by reducing visible exhaust trails.[2] Following the dissolution of the Soviet Union, production of the S-24 and its variants continued in Russia during the 1990s and 2000s to support ongoing military needs and exports.[5] Licensing agreements enabled foreign production, including in Iran where the Defense Industries Organization manufactures the Shafaq (S-24) variant for use against ground targets.[4]Design
Structure and propulsion
The S-24 rocket employs a single-stage, unguided design consisting of a cylindrical steel body with an overall length of 2.33 m (2.22 m for the rocket body) and a diameter of 240 mm. The forward section integrates the warhead assembly, while the aft portion houses the solid-propellant motor and stabilization components, enabling a modular configuration that facilitates loading onto aircraft hardpoints.[6][1] Aerodynamic stability is achieved through four fixed cranked fins at the rear, providing fin stabilization during unguided flight.[3][7] Roll is induced by seven canted exhaust nozzles on the motor, imparting a spin rate of 450–470 rpm to enhance accuracy without guidance systems. The streamlined body minimizes drag, supporting the rocket's ballistic trajectory after motor burnout. Propulsion is provided by a solid-fuel rocket motor utilizing double-based propellant, weighing approximately 46 kg in the S-24B variant, with a black powder igniter featuring twin electrical initiators for reliable startup.[6] The motor burns for about 1.1 seconds, delivering a high-thrust impulse through the canted nozzles.[1] The rocket is launched from individual underwing or underfuselage hardpoints using electrical ignition systems compatible with launchers such as the APU-68U or PU-12-40U rails, allowing integration on platforms like the Su-24 and Mi-24.[8] This setup ensures compatibility with pneumatic or pyrotechnic ejection mechanisms for safe aircraft separation.[9]Warhead and fuzing
The S-24 rocket is equipped with a high-explosive fragmentation (HE-FRAG) warhead weighing 123 kg, designed to deliver both blast and shrapnel effects against personnel, light vehicles, and unarmored targets.[1][7] The warhead casing features pre-formed grooves in hardened steel, which upon detonation produce approximately 4,000 fragments optimized for maximum area coverage and lethality.[1][3] The explosive filler consists of approximately 25 kg of high explosive, with the fragments extending the effective casualty zone to 300–400 meters in diameter.[1] These fragments are capable of penetrating up to 25–30 mm of steel armor, making the warhead suitable for engaging light armored vehicles and fortifications.[1] Fuzing options include a nose-mounted conical contact fuze for direct impact detonation, providing reliable performance against hard targets.[7] An optional KV-24 proximity fuze enables airburst detonation up to 30 meters above the ground, enhancing fragmentation effects over soft targets by dispersing the payload optimally.[1] Safety features incorporate an arming delay mechanism that activates post-launch via setback forces, preventing premature detonation during the initial flight phase from the aircraft pylon.[10]Specifications
Dimensions and weights
The S-24 rocket measures 2.33 meters in overall length when equipped with the PV-24 proximity fuze, comprising a 2.22-meter rocket body and a fuze extension.[1] Its diameter is 240 mm, providing a robust caliber suitable for air-to-ground applications.[11] The wingspan reaches 600 mm with the four deployed stabilizing fins, ensuring aerodynamic stability during flight.[1] The total launch weight of the S-24 is 235 kg, encompassing the warhead, solid-propellant motor, and structural components.[11] The high-explosive fragmentation warhead weighs 123 kg, including a 25.5 kg explosive filler.[1] Configurations with an impact fuze exhibit minor length reductions compared to the proximity-fuzed variant.[1] These dimensions influence compatibility with Soviet-era fixed-wing aircraft launchers, such as those on Su-25 and MiG-27 platforms.[11]| Parameter | Value |
|---|---|
| Overall Length (with proximity fuze) | 2.33 m |
| Body Length | 2.22 m |
| Diameter | 240 mm |
| Wingspan (fins deployed) | 600 mm |
| Total Weight | 235 kg |
| Warhead Weight | 123 kg |