Yuzhnoye SDO developed a wide range of special small-size solid propellant rocket motors (SRM), pressure accumulators (PA), and gas generators (GG) for strategic missiles and space rockets. Their design is based on a series of fundamentally new technical solutions.
They allow to solve a wide circle of technical problems:

• pop-up rocket launch;
• pop-up rocket stages separation;
• rocket deflection during pop-up launch;
• variation of geometry of nose fairing inflatable tip;
• increase in main engine nozzle altitude tolerance;
• separation of various objects and their drive-away from rocket trajectory;
• flight control of rocket parts;
• jettison of objects from rocket and ensuring their flight with specified velocity;
• spin stabilization of objects.

• High reliability;
• high resistance to operational environmental effects (temperature, vibration, humidity, electrostatic and electromagnetic fields, nuclear explosion destroying factors for military motors);
• extensive experience of successful operation on different missiles and space launch vehicles.

Range of Developed SRM, PA, and GG

By type of propellant:

• composite propellant with burn temperature of 1200 to 3300 H and aluminium content of 0 to 18%;
• bipropellant with burn temperature of 1600 to 2800 K;
• special low-temperature propellant with gasification products temperature of 800 K.

By mass of propellant charge: 0.006 to 120 kg.

By method of charge mounting:

• composite propellant-inserted and firmly fastened;
• bipropellant-inserted, glued in thermal protective cup.

By applied casing materials:

• steel with the strength of up to 1570 Mpa;
• aluminium alloy with the strength of up to 510 Mpa;
• titanium alloy with the strength of up to 1080 Mpa.

By design peculiarities:

• classical scheme (direct nozzle);
• angle of inclination of nozzle axis to motor axis: 0 to 2.36 rad;
• truncated nozzle;
• with gas diverted valve;
• one-nozzle, two-nozzle, four-nozzle, with jet dissector (for PPA);
• in the form of Segner wheel;
• ignition from nozzle side;
• ignition from electrical and mechanical pyro cartridges.

By ballistic characteristics:

• total impulse: 49 to 58860 N.s;
• thrust: 70 to 166770 N;
• operation period: 0.1 to 60 s.

By form of thrust variation diagram (flow):

• rectangular;
• digressive;
• progressive (3-20 times);
• thrust reverse with 15 Hz frequency.

RD-293 Rocket Motor

	Consists of two interlinked motors The main motor that creates thrust along the unit's axis has four thrust nozzles. The additional motor creates thrust perpendicular to the unit's axis.
	Characteristics	Values
	Propellant	bipropellant
	Vacuum thrust pulse along unit's axis, kgf	5700
	Maximal vacuum thrust, kgf.s	5000
	Operation period, s	1,1…1,6
	Mass of motors unit, kg	200
	Maximal thrust, kgf.s	4000
	Operation period, s	0,13
	Mass of motors unit, kg	67
	Diameter, mm	290
	Length, mm	1080

RD-127 Type Rocket Motors

The RD-127 type rocket motors family consists of 25 units. The motors are of the same configuration, have one mounting seat and are united into four groups by their diameter. All the motors have ignition from nozzle side. The motors family can ensure practically any value of thrust pulse within the limits of 5-300 kgf.s with 1-2% scatters.
	Characteristics	Values
	Propellant	composite
	Vacuum thrust, kgf	200…6300
	Maximal operation period, s	0,17
	Mass of motor, kg	1,15…7,49
	Diameter, mm	82…128
	Length, mm	177…282

RD-273 Type Rocket Motors

The family of motor for space objects spinning made according to the Segner wheel scheme and differing by dimensions and thrust pulse value.
	Characteristics	Values
	Propellant	bipropellant
	Vacuum thrust pulse, kgf.s	2,4…200
	Maximal vacuum thrust, kgf	7…600
	Operation period, s	0,45…0,5
	Mass of motor, kg	0,6…12
	Diameter, mm	40…125
	Length, mm	472…1830

RD-284 Type Rocket Motors

The family of four motors with the same configuration that differ only by the angle of nozzle axis inclination.
	Characteristics	Values
	Propellant	bipropellant
	Vacuum thrust pulse, kgf.s	3800
	Maximal vacuum thrust, kgf	17000
	Operation period, s	0,31…0,54
	Mass of motor, kg	63
	Diameter, mm	280
	Length, mm	820

RD-271 Rocket Motor

The motor has a truncated nozzle at the angle of 200 to motor axis.
	Characteristics	Values
	Propellant	bipropellant
	Vacuum thrust pulse, kgf.s	775
	Operation period, s	0,5…1,1
	Mass of motor, kg	9
	Diameter, mm	145
	Length, mm	562…575

PAD-213 Type Cartridge Pressure Accumulator

	The family consists of CPA of two standard sizes. It is characterized by short operation period (less than 0.15 s) and high stability of flow characteristics.
	Characteristics	Values
	Propellant	Composite
	Temperature of combustion products, K	3200
	Mass of propellant, kg	1,2…2,1
	Operation period, s	0,08…0,15
	Maximal operating pressure, kgf/cm2	170
	Diameter, mm	205
	Length, mm	349…391

PAD-215 Type Cartridge Pressure Accumulators

	The family consists of CPA of two standard sizes. It is characterized by short operation period (less than 0.15 s) and high stability of flow characteristics.
	Characteristics	Values
	Propellant	Bipropellant
	Temperature of combustion products, K	1600
	Mass of propellant, kg	0,006…0,035
	Operation period, s	0,1…1,1
	Maximal operating pressure, kgf/cm2	200…250
	Diameter, mm	42
	Length, mm	128

PAD-243 Type Cartridge Pressure Accumulators

	The PAD family consisting of 6 standard sizes characterized by progressive law of flow variation and stable characteristics.
	Characteristics	Values
	Propellant	Composite and Bipropellant
	Temperature of combustion products, K	1600…3000
	Mass of propellant, kg	1,3…120
	Operation period, s	0,4…4,5
	Maximal operating pressure, kgf/cm2	150…400
	Прогрессивность расходной характеристики (отношение максимального расхода к минимальному)	2…8
	Diameter, mm	200…810
	Length, mm	320…800

RD-186 Rocket Motor

	The family consists of two PPA standard sizes. The characteristic feature is short operation period (less than 0.15 s) and high stability of flow characteristics.
	Characteristics	Value
	Propellant	bipropellant
	Vacuum thrust pulse, kgf	74
	Maximal vacuum thrust, kgf.s	350
	Mass of propellant, kgf	0,3…0,55
	Maximal operating pressure, kgf/cm2	2,1
	Diameter, mm	94
	Length, mm	281

RD-152 Rocket Motor

Yuzhnoye SDO developed a large group of small-size solid propellant rocket motors and powder pressure accumulators that accomplish in the process of rocket launch and flight a wide circle of technical tasks to ensure pop-up launch, separation and braking of stages, drive-away from trajectory and spin stabilization of separate rocket elements, actuation of drives. The small-sire SRM and PPA may be used also to solve some national economy problems: creation of short-time small and great forces, generation of gaseous propulsive mass to actuate some mechanisms, expulsion of liquid and powder in fire-fighting equipment.