The 9M37M anti-aircraft guided missile is part of the 9K35M system and is designed to engage low-flying aircraft and helicopters at any time of year and in conditions of organized optical interference.
The 9M37M missile is designed in a symmetrical aerodynamic layout of the "Duck" type. The missile's controls (rudders) are located at the front end, and the stabilizer (wings) connected to the casing is located at the tail end. The rudders and wings are located in the same plane.
The missile has a two-channel control system, aerodynamic roll speed limitation, contact and non-contact fuse device, shrapnel-type warhead, two-stage propulsion system and onboard power supply.
Geometrically, the missile is a cylindrical shaped body with an ogival head end in a hemisphere. The nozzle of the missile is shaped like a truncated cone. The assembled missile is placed in a metal container.
The functional circuit of the missile's control circuit includes:
- A passive, optically-infrared homing head that generates control signals proportional to the angular speed of the RACETA sighting line - Target and bearing;
Homing head 9E47M. 1 - casing; 2 - electronic block; 3 - gyrocoordinator; 4 - fairing.
- autopilot with two identical control channels.
Autopilot 9B612M. 1 - electronics unit; 2 - feedback potentiometer; 3 - gearbox; 4 - steering wheel; 5 - switching board; 6 - board; 7 - bracket; 8 - BAS unit; 9 - PCB board; 10 - PCB board; 11 - target contact sensor; 12 - steering wheel unit; 13 - electric motor; 14 - tourniquet; 15 - shaft.
Structurally, the missile is made in the form of six compartments:
- bay one - homing head;
- compartment 2 - autopilot with a contact sensor for the target of the explosive device;
- bay No. 3 - combat unit with the safety executive mechanism and power supply unit located in it;
- compartment No. 4 - non-contact target sensor;
- compartment No. 5 - propulsion system with wings and a bank unit placed on it;
- compartment No. 6 - container with nitrogen power supply unit and gas generator placed on it.
Rocket compartments (without container). 1 - bay number 1 (homing head); 2 - contact target sensor; 3 - bay number 2 (autopilot); 4 - safety executive mechanism; 5 - bay number 3 (combat unit); 6 - power supply unit; 7 - bay number 4 (non-contact target sensor); 8 - bay number 5 (propulsion system); 9 - wing; 10 - roll unit.
Mechanical docking of compartments ¹1 - 5 is made by radial screws or studs with nuts that tighten the individual compartments. Compatibility of the compartments is provided by the ring burrings available to them. The junctions of the compartments are closed with metal tapes fixed with screw locks.
Electrical docking of the missile compartments is carried out by small-size plugs.
| Tactical and technical data of 9M37M missile | |
| Caliber, mm | 120 |
| The length of the rocket, mm | 2190 |
| Wingspan, mm | 360 |
| Mass of the rocket, kg | 39,2 |
| Mass of the rocket in the container, kg | 70 |
| Mass of the rocket with the container in the cork, kg | 110 |
| Weight of combat unit, kg | 3 |
| Weight of the explosive, kg | 1 |
| Tilted target range, m | between 800-1200 and 5000 |
| Defeat target on parameters, m | between 0 and 3000 |
| Average flight speed, m/s | 550 |
| Flight altitude of hit targets, km/h. | up to 1500 on counter courses, up to 1100 on catch-up courses |
| Firing restriction zone in the direction of the Sun,º | 20 |
| Explosion device | non-contact safety contact type with a range of at least 250 m from the war machine |
| The voltage of the missile's onboard network, B. | 27 |
| Homing head type | passive dual-band (optical-infrared), gyroscopic, narrowband |
| Standby time, s | 5 |
| Operating conditions (combat use and inspections), ºС | at ambient temperature from -50 to +50 and relative humidity 98% at +40 |
| Overall dimensions, mm: | |
| container | 303×320×2300 |
| caps | 400×410×2400 |