SOLID-PROPELLANT MAIN ENGINES

Main solid rocket motors

DESCRIPTION

The main functions are:

• thrust application;

• producing control force along the yaw and pitch channels with swiveling control nozzle (SCN);

• performance of all SRM characteristics under the specified external influences in every phase of operation.

These SRM are used as the first and second stages of the space launch vehicle (SLV).

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	up to 2000
Thrust, tf	up to 150
Casing	carbon fiber-reinforced plastic, cocoon type
Nozzle	swiveling control nozzle

Main SRM for short-range missile

DESCRIPTION

The main functions are:

• thrust application;

• performance of all main motor characteristics under the specified external influences in every phase of operation.

The short-range missiles are used for destroying targets within the operational range relative to the front line.

BASIC SPECIFICATIONS

Propellants	composite, high-energy
External diameter, mm	up to 1000
Thrust, tf	up to 20
Casing	carbon fiber-reinforced plastic, cocoon type
Nozzle	fixed

Main SRM for medium-range and short-range surface-to-air missiles

DESCRIPTION

The main functions are:

• thrust application;

• performance of all main motor characteristics under the specified external influences in every phase of operation.

The surface-to-air missiles used in the air defense missile system are capable of destroying various aerial targets.

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	up to 450 up to 300
Casing	high-strength steel
Nozzle	fixed

SRM for multiple launch rocket system

DESCRIPTION

Multiple launch rocket systems are one of the widespread and promising types of the ground tactical missile-artillery armament; they are capable of engaging various targets and executing various tasks depending on the head module.

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	from 122 to 400
Casing	high-strength steel
Nozzle	fixed

Main SRM for reboost stage

DESCRIPTION

It is intended for increasing payload mass injected into orbit by SLV.

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	up to 1250
Thrust, tf	up to 10
Casing	carbon fiber-reinforced plastic, cocoon type
Nozzle	swiveling control nozzle

Home Technology Solid rocket motors

Solid rocket motors

SOLID-PROPELLANT MAIN ENGINES

Main solid rocket motors

DESCRIPTION

The main functions are:

• thrust application;

• producing control force along the yaw and pitch channels with swiveling control nozzle (SCN);

• performance of all SRM characteristics under the specified external influences in every phase of operation.

These SRM are used as the first and second stages of the space launch vehicle (SLV).

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	up to 2000
Thrust, tf	up to 150
Casing	carbon fiber-reinforced plastic, cocoon type
Nozzle	swiveling control nozzle

Main SRM for short-range missile

DESCRIPTION

The main functions are:

• thrust application;

• performance of all main motor characteristics under the specified external influences in every phase of operation.

The short-range missiles are used for destroying targets within the operational range relative to the front line.

BASIC SPECIFICATIONS

Propellants	composite, high-energy
External diameter, mm	up to 1000
Thrust, tf	up to 20
Casing	carbon fiber-reinforced plastic, cocoon type
Nozzle	fixed

Main SRM for medium-range and short-range surface-to-air missiles

DESCRIPTION

The main functions are:

• thrust application;

• performance of all main motor characteristics under the specified external influences in every phase of operation.

The surface-to-air missiles used in the air defense missile system are capable of destroying various aerial targets.

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	up to 450 up to 300
Casing	high-strength steel
Nozzle	fixed

SRM for multiple launch rocket system

DESCRIPTION

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	from 122 to 400
Casing	high-strength steel
Nozzle	fixed

Main SRM for reboost stage

DESCRIPTION

It is intended for increasing payload mass injected into orbit by SLV.

BASIC SPECIFICATIONS

Propellant	composite, high-energy
External diameter, mm	up to 1250
Thrust, tf	up to 10
Casing	carbon fiber-reinforced plastic, cocoon type
Nozzle	swiveling control nozzle

Solid-propelent special engines

Pulsed control SRM

DESCRIPTION

Usage of micro SRM provides short-time control pulses along the yaw and pitch channels.

BASIC SPECIFICATIONS

Propellant	composite, high-energy
Operating time, s	0.045 … 0.05
Thrust, kgf	up to 500
Case	high-strength steel

Launch-boost SRM

DESCRIPTION

It provides high launch thrust due to usage of propellant with high specific momentum and increased combustion rate.

BASIC SPECIFICATIONS

Propellant	composite, high-energy
Operating time, s	5
Thrust, kgf	up to 8000

Roll control SRM

DESCRIPTION

It provides control force along the roll channel due to distribution valve and intrachamber pressure regulator.

BASIC SPECIFICATIONS

Propellant	composite, low-temperature
Operating time, s	75…90
Thrust, kgf	up to 30

SRM for meteorological rocket soft landing

DESCRIPTION

Usage of sloping nozzles and multigrain charge with inhibitor eliminates the thermal effect on the recoverable payload.

BASIC SPECIFICATIONS

Propellant	composite
Operating time, s	0,27
Thrust, kgf	up to 3500

Stage slowdown SRM

DESCRIPTION

Usage of sloping nozzles eliminates the influence of combustion products blast on the rocket structure.

BASIC SPECIFICATIONS

Propellant	composite
Operating time, s	0,3…04
Thrust, kgf	up to 500
Nozzle	fixed, skewed

SRM for spacecraft deployment

DESCRIPTION

It is used to perform advanced spatial maneuvers during spacecraft deployment.

BASIC SPECIFICATIONS

Propellant	composite, metal-free
Operating time, s	120…270
Thrust, kgf	up to 300-1200
Nozzle swivel angle	±60 deg