A 1C32 missile guidance station was used for radio command control of the ZUR flight, which was a coherent centimetre-band radar.
The station's antenna post (see photo) was a rather complicated turning structure, the largest element of which was the target channel antenna. To the left of it was a narrow beam antenna of the missile channel, above which was placed a wide beam antenna of the missile channel and, closer to the periphery, a command transmitter antenna to the missile. Later on, a television optical vizier camera was placed at the top of the antenna post. The station automatically rehearsed target designation information received by the telescode from the target detection station (TDC) 1C12 and made a quick search for a target. The search was conducted only by the angle of the place, as the resolution of the target detection station in the vertical plane was much lower than in the horizontal plane. After detecting a target, it was captured for auto-supervision by angular coordinates and range.
Further, the counting and resolution device at the missile guidance station determined the boundaries of the launch and kill zones, the angles of installation of antennas for the capture and tracking of LSD (with wide and narrow scanning beams), as well as the data entered into the autodalometer of the target and the missile. Telecode commands from the missile guidance station were used to turn the PU in the launch direction. After the target entered the launch area and the command transmitter was switched on, the missile was launched by pressing a button at the missile guidance station. Then the SAM was captured for escort by the signals of the defendant missile anglomer (with a wide beam) and rangefinder systems of the missile guidance station and introduced first into a narrow beam of the missile channel antenna, and then into the beam of the target channel antenna. As a result, the electric axes of both antennas were placed in parallel. Current flight control commands, formed by the counting and control unit of the missile guidance station in case of deviation of the SAM from the direction to the target, as well as a one-time command to remove the safety of the radio detonator were transmitted on board the missile.
The SAM was guided by the "half straightening" or "three points" method. The radio detonator was triggered when the missile flew less than 50 m away from the target, otherwise the missile self-destructed.
In station 1C32 was implemented a method of hidden monoconical scanning for angular coordinates and an electronic autodalometer of the target. Interference immunity was provided by the literality of channels, high energy potential of the transmitter, as well as coding of control signals.
In accordance with the design characteristics, the pulse power of the guidance station was 750 kW, the sensitivity of the receiver - 1E-13 W, beam width - 1°. Target capture for auto tracking in a non-intrusive environment could be carried out at a range up to 105 km. At a given level of interference (1.5-2 packs of dipoles per 100 m target path) the range of car support was reduced to 70 km. Errors of target tracking by angular coordinates did not exceed 0.3 degrees. (angle division, i.e. 0.06°), by distance - 15 m. Later, intermittent modes of operation were introduced for protection against Shrike missiles.
Guidance station for missiles was placed on the self-propelled "object 124", mainly similar to the chassis of the launcher.