PULSED CONTROL SRM
Usage of micro SRM provides short-time control pulses along the yaw and pitch channels
Basic characteristics:
|
Propellant |
composite, high-energy |
|
Operating time, s |
0.045 … 0.05 |
|
Thrust, kgf |
up to 500 |
|
Case |
high-strength steel |
LAUNCH-BOOST SRM
It provides high launch thrust due to usage of propellant with high specific momentum and increased combustion rate.
Basic characteristics:
|
Propellant |
composite, high-energy |
|
Operating time, s |
5 |
|
Thrust, kgf |
up to 8000 |
ROLL CONTROL SRM
It provides control force along the roll channel due to distribution valve and intrachamber pressure regulator.
Basic characteristics:
|
Propellant |
composite, low-temperature |
|
Operating time, s |
75...90 |
|
Thrust, kgf |
up to 30 |
SRM FOR METEOROLOGICAL ROCKET SOFT LANDING
Usage of sloping nozzles and multigrain charge with inhibitor eliminates the thermal effect on the recoverable payload.
Basic characteristics:
|
Propellant |
composite |
|
Operating time, s |
0,27 |
|
Thrust, kgf |
up to 3500 |
STAGE SLOWDOWN SRM
Usage of sloping nozzles eliminates the influence of combustion products blast on the rocket structure.
Basic characteristics:
|
Propellant |
composite |
|
Operating time, s |
0,3...04 |
|
Thrust, kgf |
up to 500 |
|
Nozzle |
fixed, skewed |
SRM FOR SPACECRAFT DEPLOYMENT
It is used to perform advanced spatial maneuvers during spacecraft deployment.
Basic characteristics:
|
Propellant |
composite, metal-free |
|
Operating time, s |
120...270 |
|
Thrust, kgf |
up to 300-1200 |
|
Nozzle swivel angle |
±60 deg |
LAUNCH SOLID-FUEL GAS GENERATOR
It provides the expulsion of the missile from the transportation-and-launch container during the mortar launch.
Basic characteristics:
|
Propellant |
composite |
|
Operating time, s |
2,6...3,5 |
|
Thrust, kgf |
up to 300 |
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