NSM anti-ship missile

The NSM rocket is designed according to the normal aerodynamic scheme, has a mid-range opening wing and four all-terrain rudders in the tail part of the hull (see photos 1, 2, 3, 4, 5, 6). Measures to reduce radar and thermal signature have been implemented in the missile design. The hull surface has no contrasting slits or sharp edges and composite and radio absorbent materials are widely used.

RDTT is used as the starting accelerator. The NSM missile's marching engine is a TRI 40 turbojet engine developed by the French company Microturbo. The small-size Microturbo TRI 40 single-shaft engine is equipped with a four-stage axial compressor with a pressure ratio of 3.83:1 to 5.58:1 and a circular combustion chamber. The TRI 40 develops a static take-off thrust of 2.5-3.0 kN at its own weight of 44 kg, has a maximum lateral dimension of 280 mm and length of 680 mm. The engine operates in a fairly wide flight range with the ability to maneuver in height and speed (flight height from 0 to 6000m, flight speed up to 0.95M). The engine can be started by a pyrostarter or autorotation at altitudes from 0 to 5300m with a flight speed of 0.5-0.9M. To perform the flight program and regulation, TRI 40 is equipped with a modern digital electronic-hydromechanical control system and a built-in electric generator installed on the turbine shaft. In addition to aviation kerosene JP8, the engine can run on synthetic high-calorie fuel JP10. The temperature in the combustion chamber is about 1010°C, specific fuel consumption is less than 120 kg/kN/h. The peculiarity of the TRI 40 design is the absence of a separate oil system, the bearings are lubricated with fuel.

The combat unit weighing 120 kg is a penetrating, flame-throwing one. It is equipped with a fuse with a time delay, which provides multi-variant detonation depending on the type of target.

Control system - combined. Control at the marching section of the trajectory is carried out by an inertial control system. The control system allows to operate outside of the target line of sight, the missile can move on a complex pre-programmed trajectory, round obstacles on the ground and air defense areas of the enemy, to attack the target in the most vulnerable sectors. The missile's trajectory correction in the march area is based on data from the GPS satellite navigation subsystem and the TERCOM (Terrain Contour Matching) terrain correction subsystem. The principle of TERCOM operation is based on comparing the terrain of a particular area where the missile is located with reference maps of the terrain along the route of its flight, previously stored in the memory of the onboard control system.

The missile provides for the installation of a new noise-immune thermal imaging head of homing with increased sensitivity and an enhanced sector of view. According to experts, this SOS will allow to detect a target even if its thermal field is reduced with the help of a universal water protection system. The autonomous target selection is performed by comparing the target image from the CNS sensor with standard target image templates stored in the onboard control system memory.

The missile is delivered in a 4 x 0.81 x 0.8m container. The curb weight of the container is 710 kg. The time between scheduled inspections is 3 years and between overhauls is 5-10 years. Planned time of missile operation - 30 years.