In order to arm E-152 interceptor-fighter powered by R-15-300 engine, the Mikoyan Design bureau developed K-9 guided rocket intended to hit targets under all aspect angles, including head-on and crossing course. Rocket homing by parallel approach procedure, providing zero angular velocity of line "rocket-target", was selected to minimise rocket acceleration, particularly in the vicinity of targets attacked under all aspect angles. The rocket had a symmetric X-shape aerodynamic configuration with tiltable wing. Longitudinal control is performed by tiltable wing. Four ailerons attached to fixed stabiliser provide roll control. Four rollerons are installed on the stabilisers to increase roll damping. Rocket main equipment consists of: ZR-1 semi-active pulsed radar seeker, APZ-18 autopilot, ZRV-1 pulsed radio fuse, blast-fragmentation warhead, I-60 safety mechanism and PRD-56 single-chamber double-mode powder engine.
Following versions of the K-9 rocket were prepared for flight tests:
- rocket armed with warhead (item 90);
- ballistic rocket (item 91) destined to assess aerodynamic and ballistic characteristics of the rocket with fixed wing in flight, to check safe rocket separation from aircraft and to determine engine characteristics;
- rocket controlled by a program (item 92) destined to assess aerodynamic and ballistic characteristics of the rocket controlled by a program in flight, as well as to check autopilot, power unit and pneumatic system in flight;
- rocket equipped with telemetry system (item 93) destined to assess closed loop (aircraft-rocket-target) performance of the rocket, fitted out with a warhead and radio fuse, in flight close to the target without warhead explosion.
26 rockets were produced in 1961 (item 90 - 3 rockets, item 91 - 6 rockets, item 92 - 11 rockets, item 93 - 6 rockets). Three K-9 firing were made in early 1961, using a launcher mounted on a ground test rig. Ten K-9 rocket launches (5 - item 91 and 5- item 92) were made from the E-152A aircraft during the flight tests in 1961. Test results confirmed compliance of the rocket aerodynamic and ballistic characteristics with estimated ones. Warhead ground tests at GSKB-47 test range, bench tests of rocket systems, mathematics simulation and modelling of all rocket flight modes, rocket operational efficiency calculation, made by NII-2, and other tests and checks were carried out.
|Tracking system||Semiactive Radarhoming|
|Dimensions & Weight|
|Warhead weight, kg||27|
|Speed, m/s (km/h)||1400 (5000)|
|Launch range, km||9|
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