K-10S (AS-2 Kipper) Kometa-10 ", "product 352",
The AS-2 air-to-surface missile is a supersonic, turbojet-powered, low-level run-in, cruise missile with a range of 30 to 100 nm. The K-10S missile (Article 352), developed especially for the Tu-16K-10 (Badger-C) as an anti-ship weapon, was in October 1961, together with that aircraft certified for ordnance. One K-10S missile is suspended from the aircraft, under the middle section of the fuselage. It carries either a conventional or a nuclear 2200-lb warhead. The missile weighs approximately 9120 pounds.
Yhe K-10 Air-Launched Cruise Missile of class "air-surface" was accepted to the armament in 1961. It has the turbojet engine, which is established in the lower part of the fuselage, the system of beam-rider guidance + OF ARLGSN in the last stage of flight. Glider - all-metal monoplane with those be cantilevereding (arrow-shaped form) by wing and tail assembly. Wings are added with the storage and the transport. Fairing about the honeycomb construction. Basic materials, used with the production of the glider: D -16T, AMG-', ML -5, AL -8, Y2KH2NVFA. Cast in block knots: stabilizer, keel, power frames (magnesium loam casting).
With the production of rocket K-10 the production of the fairings about the honeycomb construction was new technological process. Their molding was produced into several stages. Internal and outer casings were formed with at first vacuum method on the steel punches. In parallel on the special equipment honeycomb fillers from the fiberglass fabric were made. To the internal jacket (also on the punch) of priformovyvalsya honeycomb filler, then dressed the formed outer casing and belt; all this was placed into the furnace, where on the three-stage temperature conditions was conducted polymerization. But not all was smoothly, went the marriage: bubbles, stratification and other defects. The search for the solution of these problems began. Active part in it took such key personnel, as A.I.Pushkin, A.I.Babanin, A.S.Zazakov, N.V.Kashcheyev, I.V.Pavlov (VIAM - ALL-UNION SCIENTIFIC RESEARCH INSTITUTE OF AVIATION MATERIALS), M.Z.Eydlin and V.I.Lagutin (BAR). Process was fixed, and the production of articles was provided for.
The aircraft was equipped with a powerful radar with two-channel detection and guidance equipment. Instead of the navigator's cabin and the former "bomber" radar "Rubidium", the antenna and target channel equipment were placed in the voluminous nose fairing (see photo), which ensured the detection and tracking of a large target from a distance of up to 400 km, in the ventral fairing there was a missile channel antenna, which served for its guidance and correction at the initial stage of the flight. The station operator's workplace was equipped in a special pressurized cabin in the cargo compartment (similar to how it was done on the Tu-16KS). To accommodate the K-10 rocket, the cargo compartment itself was lengthened and equipped with a BD-238 beam holder, and tank No. 3 was dismantled in the fuselage. The aircraft also received more powerful power supplies necessary to ensure the operation of the radar, on-board systems and missile equipment. The control system of the complex - K-10U - included the radar of the carrier aircraft and the systems placed on the rocket were developed by KB-1 under the leadership of S.F. Matveevsky). The rocket used an autopilot with an aneroid altimeter and command course correction from the carrier on the marching section and ARS GOS at the final stage (homing range of ARS GOS 15-20 km). The tactical and technical assignment for the development of the missile contained the requirement to provide a salvo launch of several missiles at one target with a complex route to reach the target. A two-channel target detection and tracking radar on a carrier ("EN") provided target detection, and a missile correction radar on a carrier provided a correction of the missile's course at the initial stage.
The K-10S cruise missile was an unmanned projectile with a swept wing and empennage, distinguished by an original layout scheme with a ventral engine. As a power plant, taking into account the required range, the M-9FK turbojet engine was used - a short-life version of the common RD-9B, which was distinguished by the absence of a number of units, but equipped with an afterburner and a starter-generator necessary to power the onboard equipment for a fairly long flight (up to 10 minutes). The projectile wing with a sweep angle of 1/4 chords 55 ° was similar to those previously used on projectile aircraft KS, Kh-20, as well as on manned aircraft I-350, MiG-19 and a number of others. With low requirements for maneuverability for the K-10S, a small wing area turned out to be sufficient. The ailerons were deflected by an angle of up to ±10° from the neutral position. In the absence of flaps, the ailerons were located not near the wingtips, but approximately in the middle of its half-span, which met both the requirements for controllability along the roll channel and the need to reduce the bending moment acting on the not too rigid wing structure. During transportation and operation, the wing consoles folded. The control system of the complex - K-10U - included the radar of the carrier aircraft and systems placed on the rocket. The rocket used an autopilot with a barometric altimeter and command course correction from the carrier on the marching section and ARS GOS at the final stage (homing range of ARS GOS 15-20 km). Vuh-channel target detection and tracking radar on the carrier ("EN") provided target detection, and the missile correction radar on the carrier provided the missile course correction at the initial stage. The target detection range of the carrier is 400 km. After launching from a carrier, the rocket sank in height by 1000-1500 m, after which it kept the flight altitude using an aneroid altimeter. At the 70th second of the flight, the missile control was transferred to command mode according to the radar data on the carrier. At a distance of 105 km from the target, on command from the carrier, the missile entered a gentle dive at an angle of 13-18 degrees to a height of 2400 m, after which the dive became even more gentle (3-8 degrees) to a height of 800-1200 m. At flight level 800 -1200 m for 15-20 km from the target, on command from the carrier, the ARS GOS of the missile was turned on, captured the target and chose the trajectory along the shortest path. The missile maneuvered during the flight, but the missile did not have any algorithms for overcoming air defense.
For guidance, it uses a preprogrammed autopilot for launch and climb, an autopilot with command correction for mid-course flight, and active radar for terminal flight. The guidance system combines inertial guidance during the initial flight stage and active-radar homing close to the target. The missile can carry a 350kt nuclear warhead. It has a CEP of 150 ft when used in an anti-ship role and a CEP of 1 to 2 nm when used against land targets. The warhead - FK-10 (high-explosive-cumulative) ensured the destruction of ships with a displacement of up to 10,000 tons.
However, there were questions about the reliability and complexity of operating the guidance system. According to calculations, to destroy an aircraft carrier group with missiles only with conventional warheads, a group flight of one regiment of Tu-16K10 aircraft is required. However, the use of nuclear warheads will reduce the number of aircraft. The K-10-26 missile system remained in service until the last years of the existence of Soviet naval aviation. By the end of 1981, there were about 200 Tu-16K-10s in the USSR naval aviation - about 40% of all Tu-16s in service with the fleet. By the time of the collapse of the USSR, another 38 missile carriers continued to serve in the Crimea, and another 34 vehicles were in the Northern Fleet. The final decommissioning of the K-10 complex occurred with the decommissioning of the Tu-16 aircraft in 1994.
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