Designed to destroy strategic targets at intercontinental ranges. Adopted for service with the Navy in 1986. Installed on the strategic missile-carrying submarines project (667BDRM) having a basic load of 16 missiles.
The missile comprises a number of new technical designs:
- three-stage missile of silo-limited dimensions;
- application of a high-accuracy astro-inertial control system and “GLONASS” navigation satellite radio correction system substantially increased the firing accuracy;
- various flight trajectories at minimum and intermediate firing ranges and dispensing of re-entry vehicles within an arbitrary zone can be realized ;
- operational capabilities of missiles were improved due to the possibility of launching from high latitudes of Arctic.
Two-stage liquid-fuel sustainers are “submerged” in the missile fuel tanks. The design feature of the missile is integration of the 3rd stage propulsion systems and the warhead into a single unit with common tanks. The front section of the missile houses an instrument section with the missile control system, which includes: equipment for astro-correction of the flight trajectory according to the results of measurement of navigation star coordinates, devices for radio correction according to the results of exchanging information with navigational satellites and reentry vehicles.
The all-welded missile body is made of an aluminum-magnesium alloy.
The 1st stage engine consists of two units: main (single-chamber) and steering (four-chamber) engines. Pitch, yaw and roll control is provided by turning the combustion chambers of the steering unit.
The 2nd stage body consists of an oxidizer tank connected with the 1st stage body and a fuel tank whose front bottom is of a conoidal shape used for accommodation of the reentry vehicles and 3rd stage engine.
The 2nd stage engine is a single-chamber one. Its main components are accommodated in the 1st stage oxidizer tank, pitch and yaw control is provided by turning the gimbaled combustion chamber, and roll control, by the roll unit.
The 3rd stage engine is a single-chamber one. The 3rd stage control in all channels is provided by the dual-mode reentry vehicle dispensing engine operating concurrently with the 3rd stage engine.
The 1/2 and 2/3 stages separation is accomplished by the extended explosive charges.
To mate the missile with the launcher the tail section of the missile is provided with the load-bearing belt (adapter).
After missile takeoff the adapter remains on the launch pad.
| Basic characteristics |
Mass, t:- takeoff
- maximum throw weight
|
|
| Maximum firing range |
intercontinental |
| Warhead |
MIRVed |
| Number of reentry vehicles |
4 |
| Control system |
astro-radio-inertial |
| Number of stages |
3 |
| Missile length, m |
14.8 |
| Diameter of 1st and 2nd stages, m |
1.9 |
| Diameter of 3rd stage, m |
1.85 |
|
