KSR-2
The KSR-2 was developed based on the KSR rocket, as a successor to the imperfect KS-1 Kometa, under Decree 998-435 of 22 August 1959. It was a massive, long and heavy missile, designed for heavy aircraft. It was designed against large ships, but also against ground targets such as bridges. It became the first Soviet production missile to be powered by a liquid-fuel rocket engine.
The Soviet Union went down the route of using liquid propellants in missiles (instead of the solid ones used in the US), despite the practical problems posed by their use. Most of these substances (usually both fuel and oxidizer) are highly aggressive, possibly poisonous or explosive. Handling them is therefore difficult and dangerous. On the other hand, engines powered by them offer high performance.
The overall concept of the KSR-2 is more similar to the K-10 than to the KS-1; unlike the KS-1 (which looked like a small aircraft), the KSR-2 already had a more classic "rocket" configuration - a slender cigar-shaped body, but with large wings and tail surfaces it still somewhat resembled an airplane. Unlike the K-10, it did not have a jet engine mounted under the fuselage; propulsion was provided by a rocket engine located directly in the fuselage of the KSR-2. This arrangement had the advantage of less weight and also made handling the missile easier. Unfortunately, this ease was more than offset by the fact that the engine required filling with corrosive and highly toxic substances, making operational use of the missile very problematic. The propellant, designated TG-02 (also TT-S2), was a self-igniting substance, the oxidizer was AK-20F. The Isaev S2.721V rocket engine itself (chief designer Alexey M. Isaev) had two modes of operation and two combustion chambers, located in the rear of the fuselage. After the missile was released from the carrier, the engine first began operating in acceleration mode with a thrust of 11.77 - 11.97 kN (1200-1220 kg). After the missile began to guide the target, the combustion in one of the chambers was stopped and the engine operated in cruise mode with a thrust of 6.67-6.87 kN (680-700 kg). The wings were about half the length and height of the fuselage, sloping down 5 degrees to the ends, with two aerodynamic fins on each half. The tail surfaces were of the classic "airplane" type, not floating. The vertical tailplane had a 62 degree arrow, the horizontal surfaces 55 degrees. At the tip of the vertical tailplane there was an antenna for mid-flight control. A cover for the fuel line ran along the bottom of the fuselage. The serial missiles were light grey throughout, except for the darker radome.
The navigation and control system was similar to that of the KS-1, developed by OKB-286. End guidance was provided by a K-2 radar mounted in the nose, the autopilot was designated APK-5B.
Unlike the previous K-1 Kobaľt-N (Cobalt) system on the Tu-16KS (on the KS-1), the Tu-16KSR-2 with the Rubin-1K (Ruby) system was equipped with more sophisticated electronics. This automated some operations that had to be performed manually on the previous generation. This allowed the preparation of the missile for launch and other necessary tasks to be handled by the aircraft's navigator, and no longer required a dedicated radar operator as on the TU-16KS. The radar had a range of about 200 km against a cruiser category target, 250 to 290 km against a hydroelectric plant, and 130 to 180 km against a bridge.
The guidance method differed from the KS-1, where the carrier irradiated the target throughout the missile's flight. The carrier's radar, which in the newer version was the Rubikon-1K, located the target (range approximately 300-350 km) and relayed the information to the KSPM radar in the missile's nose, which locked onto the target before firing. After the KSPM radar picked up the target, the navigator switched to guidance by the missile's own system. Once the missile was launched, the carrier no longer had to worry about missile guidance.
The aircraft could carry one or two missiles, which could be launched separately (even at different targets) or simultaneously. The powerful warhead of the FK-2 was capable of penetrating armour with a thickness of 300 mm. Another variant of the warhead, the FK-2N, was designed against ground targets. There was also a nuclear (special) warhead.
The KSR-2 missile was part of the K-16 attack system, which consisted of a Tu-16KSR-2 aircraft with a Rubin-1K search/guidance radar and two KSR-2 missiles carried on BD-352 hangers under the wings. Testing began in 1958, with a prototype Tu-16KSR-2, modified from a production Tu-16KS (49 red, number 7203608), serving as the carrier. Modifications included, for example, cutouts in the outer sections of the flaps to prevent contact with the missile's tail surfaces during use.
After four years (in 1962), the system was adopted into the Soviet Navy's (VMF) armament. Another user was Egypt, which purchased several Tu-16KSR-2s with armament and deployed them against Israel in October 1973 during the Yom Kippur War.
The original KSR-2 was followed by another version of the missile, designated KSR-2M, used on new versions of aircraft in VMF service - notably the Tu-16K-11-16, Tu-16KSR-2-5. The improved KSR-2M used elements from the then newly developed KSR-5, especially the new Isaev S5.6.0000 engine, thus the minimum launch altitude dropped from 1,500 m to 500 m. A new variant of the K-16 system with the KSR-2M missile was accepted into service in 1967.
A by-product of the development of the KSR-2 was the KRM-2 (krylataya rocket-mišeň, i.e., cruise missile-target) remotely controlled training target, also designated MV-1 (asi mišeň-vysotnaya, i.e., high-altitude target). The KRM-2 was intended for training the USSR's air defense forces (PVO). It has a modified nose section (without the K-2 homing radar), and a different rear section with a new Tumansky R209-300 rocket engine (also liquid-fueled). The horizontal tail surfaces had additional small stabilizing arrow-shaped vertical surfaces, the upper part of the vertical tail surface carried a significantly larger cover than that of the KSR-2. The KRM-2 had a maximum range of 376 km, a maximum speed of 2760 km/h (at 22,500 m), a maximum range of 25,000 m, and a straight flight duration of 433 seconds. The carrier was a special version of the Tu-16KRM, and either the Tu-16KSR-2 or other versions of the Tu-16 were modified to this version.
[The KSR-2KSR-2 cruise missile
Sources:
Yefim Gordon - Soviet/Russian Aircraft Weapons, Midland publishing, 2004
A. B. Shirokorad - Encyclopedia of the Russian Rocketry 1817-2002, ACT Moscow, Charvest Minsk, 2003
Yefim Gordon, Vladimir Rigmant - Tupolev Tu-16 Badger, Aerofax, 2004
The KSR-2 was developed based on the KSR rocket, as a successor to the imperfect KS-1 Kometa, under Decree 998-435 of 22 August 1959. It was a massive, long and heavy missile, designed for heavy aircraft. It was designed against large ships, but also against ground targets such as bridges. It became the first Soviet production missile to be powered by a liquid-fuel rocket engine.
The Soviet Union went down the route of using liquid propellants in missiles (instead of the solid ones used in the US), despite the practical problems posed by their use. Most of these substances (usually both fuel and oxidizer) are highly aggressive, possibly poisonous or explosive. Handling them is therefore difficult and dangerous. On the other hand, engines powered by them offer high performance.
The overall concept of the KSR-2 is more similar to the K-10 than to the KS-1; unlike the KS-1 (which looked like a small aircraft), the KSR-2 already had a more classic "rocket" configuration - a slender cigar-shaped body, but with large wings and tail surfaces it still somewhat resembled an airplane. Unlike the K-10, it did not have a jet engine mounted under the fuselage; propulsion was provided by a rocket engine located directly in the fuselage of the KSR-2. This arrangement had the advantage of less weight and also made handling the missile easier. Unfortunately, this ease was more than offset by the fact that the engine required filling with corrosive and highly toxic substances, making operational use of the missile very problematic. The propellant, designated TG-02 (also TT-S2), was a self-igniting substance, the oxidizer was AK-20F. The Isaev S2.721V rocket engine itself (chief designer Alexey M. Isaev) had two modes of operation and two combustion chambers, located in the rear of the fuselage. After the missile was released from the carrier, the engine first began operating in acceleration mode with a thrust of 11.77 - 11.97 kN (1200-1220 kg). After the missile began to guide the target, the combustion in one of the chambers was stopped and the engine operated in cruise mode with a thrust of 6.67-6.87 kN (680-700 kg). The wings were about half the length and height of the fuselage, sloping down 5 degrees to the ends, with two aerodynamic fins on each half. The tail surfaces were of the classic "airplane" type, not floating. The vertical tailplane had a 62 degree arrow, the horizontal surfaces 55 degrees. At the tip of the vertical tailplane there was an antenna for mid-flight control. A cover for the fuel line ran along the bottom of the fuselage. The serial missiles were light grey throughout, except for the darker radome.
The navigation and control system was similar to that of the KS-1, developed by OKB-286. End guidance was provided by a K-2 radar mounted in the nose, the autopilot was designated APK-5B.
Unlike the previous K-1 Kobaľt-N (Cobalt) system on the Tu-16KS (on the KS-1), the Tu-16KSR-2 with the Rubin-1K (Ruby) system was equipped with more sophisticated electronics. This automated some operations that had to be performed manually on the previous generation. This allowed the preparation of the missile for launch and other necessary tasks to be handled by the aircraft's navigator, and no longer required a dedicated radar operator as on the TU-16KS. The radar had a range of about 200 km against a cruiser category target, 250 to 290 km against a hydroelectric plant, and 130 to 180 km against a bridge.
The guidance method differed from the KS-1, where the carrier irradiated the target throughout the missile's flight. The carrier's radar, which in the newer version was the Rubikon-1K, located the target (range approximately 300-350 km) and relayed the information to the KSPM radar in the missile's nose, which locked onto the target before firing. After the KSPM radar picked up the target, the navigator switched to guidance by the missile's own system. Once the missile was launched, the carrier no longer had to worry about missile guidance.
The aircraft could carry one or two missiles, which could be launched separately (even at different targets) or simultaneously. The powerful warhead of the FK-2 was capable of penetrating armour with a thickness of 300 mm. Another variant of the warhead, the FK-2N, was designed against ground targets. There was also a nuclear (special) warhead.
The KSR-2 missile was part of the K-16 attack system, which consisted of a Tu-16KSR-2 aircraft with a Rubin-1K search/guidance radar and two KSR-2 missiles carried on BD-352 hangers under the wings. Testing began in 1958, with a prototype Tu-16KSR-2, modified from a production Tu-16KS (49 red, number 7203608), serving as the carrier. Modifications included, for example, cutouts in the outer sections of the flaps to prevent contact with the missile's tail surfaces during use.
After four years (in 1962), the system was adopted into the Soviet Navy's (VMF) armament. Another user was Egypt, which purchased several Tu-16KSR-2s with armament and deployed them against Israel in October 1973 during the Yom Kippur War.
The original KSR-2 was followed by another version of the missile, designated KSR-2M, used on new versions of aircraft in VMF service - notably the Tu-16K-11-16, Tu-16KSR-2-5. The improved KSR-2M used elements from the then newly developed KSR-5, especially the new Isaev S5.6.0000 engine, thus the minimum launch altitude dropped from 1,500 m to 500 m. A new variant of the K-16 system with the KSR-2M missile was accepted into service in 1967.
A by-product of the development of the KSR-2 was the KRM-2 (krylataya rocket-mišeň, i.e., cruise missile-target) remotely controlled training target, also designated MV-1 (asi mišeň-vysotnaya, i.e., high-altitude target). The KRM-2 was intended for training the USSR's air defense forces (PVO). It has a modified nose section (without the K-2 homing radar), and a different rear section with a new Tumansky R209-300 rocket engine (also liquid-fueled). The horizontal tail surfaces had additional small stabilizing arrow-shaped vertical surfaces, the upper part of the vertical tail surface carried a significantly larger cover than that of the KSR-2. The KRM-2 had a maximum range of 376 km, a maximum speed of 2760 km/h (at 22,500 m), a maximum range of 25,000 m, and a straight flight duration of 433 seconds. The carrier was a special version of the Tu-16KRM, and either the Tu-16KSR-2 or other versions of the Tu-16 were modified to this version.
[The KSR-2KSR-2 cruise missile
| Parameter[/baa] | ]KSR-2 |
|---|---|
| Code Designation | AS-5A Kelt |
| [baa]Entry from Service | 30. 12. 1962 |
| Length (m) | 8.647 (8.62) |
| Wingspan (m) | 4.522 |
| Wing angle | 55 degrees |
| Fuselage diameter (m) | 1.0 |
| Starting weight (kg) | 4 077 |
| Head weight (m)[/b:750 (850) | |
| Range (km) | 160 |
| Launch height (m) | 4,000 - 10,000 |
| Flight altitude (m) | Descent trajectory |
| Speed (km/h) | 1 250 |
| Engine | Isaev S2.721V |
| Carrier | Tu-16KSR-2, Tu-16K-11-16, Tu-16KSR-2-5, Tu-16K-26 |
Sources:
Yefim Gordon - Soviet/Russian Aircraft Weapons, Midland publishing, 2004
A. B. Shirokorad - Encyclopedia of the Russian Rocketry 1817-2002, ACT Moscow, Charvest Minsk, 2003
Yefim Gordon, Vladimir Rigmant - Tupolev Tu-16 Badger, Aerofax, 2004
