CEB-2 cruise missile (K-16 complex)

According to the KAC-2 aerodynamic scheme - a monoplane with a mid-wing and plumage (see diagram). The rocket glider consists of an all-metal fuselage, wing and plumage.  Wing with a sweep of 55 ° folded during storage and transportation of the missile (see photo). The main material in the construction are aluminum alloys, dural and steel, as well as plastics.

The active radar CNS of KS-2M type had a target acquisition range of up to 160 km (see the layout diagram). The bow radio transparent fairing is made of two layers of fiberglass with honeycomb fiberglass filler. Behind the ARLGSN compartment there is a warhead compartment (BC), in which nuclear or high-explosive batteries of FC-2 type could be installed. The latter had 681 kg of explosives with a total weight of 840 kg and pierced 300 mm ship's armor. For the destruction of ground targets was designed combat unit FC-2H - blast with an active shell.

Behind the BC compartment were located: an oxidizer tank with a capacity of 990 l (1570 kg) and a fuel tank for 630 l (530 kg). TG-02 composition was used as a fuel; AK-20I oxidizer was a solution of nitrogen tetraoxide in concentrated nitric acid. Fuel was supplied to the two-mode LRD C2.721B (later C5.6.000) by turbo-pump unit. The LRD had two modes of operation - starting with a thrust of 1215 kgf and marching with a thrust of 710 kgf. The engine was started at the moment of detaching the projectile at all launch altitudes from 4 to 10 km and carrier speed 400 - 500 km/h.

Between the tanks and the engine is located equipment compartment with pneumatic autopilot AP-72-4, ampoule silver-zinc battery (designed for 500s work), electrical special equipment and air cylinders.

The launch range of the KSW-2 missiles was 160-170 km (see the guidance diagram). The target was a car escort 20-30 km before the missile launch point. In contrast to the Comet, the target was taken by a car escort for an airborne missile radar, not an airplane. In this case, it was possible to direct both missiles to the same target or choose for each of its targets. The missiles were detached one by one. In 7c after detachment the engine was started and acceleration started. The drawdown of the rocket after separation from the aircraft was 600-1200m depending on the height and speed of flight. After 40 c after detaching the time mechanism gave the command to connect the rocket autopilot to the homing radar KS-11M, and the engine was switched to marching mode. By this time the rocket speed reached 1250 km/h. As the missile approached the target at a distance of 15 km station K-11M gave the command to deploy gyroscopes, and the missile control was carried out taking into account the speed of the target. The same command was used to unlock the locking device of the antenna, and after its optical axis was combined with the longitudinal axis of the missile, stopped again. In this mode, the K-11M station operated until the end of the missile's flight. When the target was 450m away, K-11M would issue a command to disable radio control and the missile would continue to fly, maintaining the last position for another 1.2-1.6s, after which it would dive.

KCR-2M

The upgraded KSR-2M missile is designed for low-altitude launches. KCR-2M was equipped with a new dual-mode LCD C5.6.0000.0 (see photo) developed by the Isayev Design Bureau of Chemical Engineering.  The autopilot reduced the missile drawdown after the detachment to 150-200 m. After the launch of the LRBM, the rocket smoothly gained an altitude of 500-800 m above the launch vehicle, then moving on to an inclined trajectory controlled by the GSN, with a practical launch range of no more than 70-80 km.

KCR-11 (product 086)

A new autonomous guidance system with a passive self-guided radar head (PARGSN) has been developed for the KCR-11 missile.  The passive radar coordinator of the 2RPG-10 target with a target detection range of up to 350 km was used as the SARSAT-11.   Structurally, KSW-11 differed from the prototype by the design of fuel intake in tanks, the inner frame of the fuselage. To be placed on the carrier, KSR-11 was equipped with additional suspension units, and the carrier with beam holders DB-352. The missile was launched at a range of 160-170 km. The range of the Tu-16K-11 complex with one missile was 2000 km, the probability of hitting the target was 0.8-0.9.

Missiles guidance (see diagram) was carried out by a combined method - the enemy radar was detected by an airborne target reconnaissance station "Ritza".  "Ritsa" detected both observation radars of air defense systems at a distance of 300-350 km, and gun pointing stations at a distance of up to 270 km. The station determined the range, azimuth, radiation frequency, periodicity and duration of pulses. PARGSN missiles were tuned to the frequency of target radiation and took it to the car escort. After detaching the missile flight was in passive mode from the autopilot, from the 40th second included in the work of the PARGSN, performing pointing on the course. In addition to the normal trajectory, there was a possibility of a mode, when the WRD worked until the 60th second in the launch mode and the missile was gaining altitude. With an angular misalignment of the target at 25°, the missile went into a dive to the target with self-guided guidance on course and pitch. When the radar ceased to operate, the CNS target missile kept its flight direction for 25 seconds. A disadvantage of CEB-11 was the limited frequency range of its PAROS, which excluded the use of the missile on a number of ship's radars.

At sea trials, it was planned to use the KCR-11 missile in conjunction with KCR-2.