KSR-2 / KS-11 / KSR-II / AS-5 KELT - Design/h1>
According to the aerodynamic scheme, the KSR-2 is a monoplane with a mid-wing and plumage (see diagram ). The rocket airframe consists of an all-metal fuselage, wing and plumage. The wing with a sweep of 55 ° was folded during storage and transportation of the rocket (see photo ). The main material in the design are aluminum alloys, duralumin and steel, as well as plastics.
The active radar seeker of the KS-2M type had a target acquisition range of up to 160 km (see layout diagram ). The radio-transparent nose fairing is made of two layers of fiberglass with honeycomb fiberglass filler. Behind the ARLGSN compartment is a warhead compartment (warhead), in which a nuclear or high-explosive-cumulative warhead of the FK-2 type could be installed. The latter had 681 kg of explosives with a total weight of 840 kg and pierced 300 mm ship armor. To destroy ground targets, the FK-2N warhead was intended - high-explosive with an active shell.
Behind the warhead compartment were located: an oxidizer tank with a capacity of 990l (1570kg) and a fuel tank for 630l (530kg). The composition TG-02 was used as fuel, the oxidizer AK-20I was a solution of nitrogen tetroxide in concentrated nitric acid. Fuel was supplied to the dual-mode LRE C2.721V (later C5.6.000) by a turbopump unit. The rocket engine 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 the projectile was uncoupled at all launch altitudes from 4 to 10 km and carrier speeds of 400-500 km/h.
Between the tanks and the engine there is an equipment compartment with an AP-72-4 pneumatic autopilot, an ampoule silver-zinc storage battery (designed for 500 s of work), blocks of electrical equipment and air cylinders.
The launch range of KSR-2 missiles was 160-170 km (see diagramguidance). The target was taken for auto tracking 20-30 km to the missile launch point. Unlike the "Kometa", the target was taken for auto-tracking of the onboard radar of the missile, and not of the aircraft. In this case, it was possible to direct both missiles at one target or choose a target for each. The uncoupling of the missiles took place in turn. 7s after the cutoff, the engine was started and acceleration began. The rocket landing after separation from the aircraft was 600-1200m, depending on the altitude and flight speed. 40 seconds after the uncoupling, the time mechanism issued a command to connect the missile's autopilot to the KS-11M homing radar, and the engine was switched to the marching mode.
By this time, the speed of the rocket reached 1250 km / h. With the approach of the missile to the target at a distance of 15 km, the K-11M station issued a command to open the gyroscopes, and the missile was controlled already 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 aligned with the longitudinal axis of the rocket, it was locked again. In this mode, the K-11M station worked until the end of the rocket flight. When 450m remained to the target, the KS-11M station issued a command to turn off the radio control, and the rocket continued flying, maintaining the last position for another 1.2-1.6s, after which it switched to a dive.
Their targets were the escort ships of the aircraft carrier group. The possibility of using the KSR-2 on aircraft carriers was also considered, but this required at least 40-60 missiles - a volley of an entire regiment. Nine regiments of the KSR-2 Long-Range Aviation received both conventional and nuclear warheads - they could be used against both ground and sea targets.
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