SR ROCKETs

Stalker

SPECIFICATIONS

Small-lift launch vehicles

Payload to 200 km LEO

Payload to 400 km SSO

1700 kg

1300kg

A two-stage, small-lift launch vehicle for commercial launches. The rocket was designed according to market needs

700 kg

Specifications

Stalker

FIRST STAGE

Launch mass

Length

60,5 t

32,8 m

Diameter

2,2 m

Propellants

First stage length

oxygen and methane

18,5 m

Second stage length

6,25 m

Target launch cost

8 350 ths $

Stalker

SPECIFICATIONS

First stage

The propulsion system of the first stage is equipped with 9 engines that were built according to the open cycle layout. Oxygen and methane are used as propellant

First stage length

18,5 m

Thrust: sea level

76,5 tf

SECOND STAGE

Stalker

Thrust: vacuum

86,4 tf

Specific impulse: sea level

300,0 Isp

Specific impulse: vacuum

339,2 Isp

PAYLOAD FAIRING

FIRST STAGE

Second stage

Stalker’s second stage is equipped with one RD-3,5 engine

Second stage length

6,25 m

Stalker

Thrust: sea level

11,0 tf

Specific impulse: vacuum

360,0 Isp

SECOND STAGE

ENGINE

Payload fairing

Stalker

2,2 m

Payload fairing diameter

Payload fairing length

5,2 m

The launch vehicle is designed with the possibility of using two payload fairings. SR Space works on composite materials that will be used to manufacture the rocket

Extended payload fairing diameter

3,2 m

Extended payload fairing length

8 m

PAYLOAD FAIRING

Engine

The RD-1 liquid-propellant rocket engine is built according to the open cycle layout. Oxygen and methane are used as propellant.

Thrust: sea level

8,5 tf

Stalker

Thrust: vacuum

9,6 tf

The engine is designed to be reused during several missions

Specific impulse: sea level

300,0 Isp

Specific impulse: vacuum

339,2 Isp

SR ROCKETs

Cosmos

A two-stage ultra-small launch vehicle designed to launch small spacecraft into orbit

SPECIFICATIONS

Ultra-small-lift launch vehicle

Payload to 200 km LEO

Payload to 400 km SSO

390 kg

310 kg

Payload to 700 km SSO

200 kg

Specifications

Cosmos

FIRST STAGE

Launch mass

Length

13,5 t

22 m

Diameter

1,2 m

Propellants

First stage length

oxygen and methane

13 m

Second stage length

6 m

Target launch cost

1 670 ths $

Cosmos

SPECIFICATIONS

First stage

First stage length

13 m

Cosmos

Thrust: sea level

3,03 tf

Cosmos’s first stage is equipped with one RD-3,5 engine that was built according to the open cycle. Oxygen and methane are used as propellant

SECOND STAGE

Thrust: vacuum

3,56 tf

Specific impulse: sea level

294,8 Isp

Specific impulse: vacuum

346,8 Isp

FIRST STAGE

Second stage

Second stage length

6 m

Cosmos

Cosmos’s second stage is equipped with one liquid-propellant engine RD. Oxygen and methane are used as propellant

PAYLOAD FAIRING

Thrust: vacuum

1,0 tf

Specific impulse: vacuum

348,1 Isp

SECOND STAGE

Payload fairing

SR Space works on composite materials that are used to manufacture the payload fairing

Cosmos

ENGINE

Payload fairing diameter

1,2 m

Payload fairing length

3 m

Engine

The RD-3,5 liquid-propellant rocket engine is built according to the open cycle layout. Oxygen and methane are used as propellant.

Thrust: sea level

3,03 tf

Cosmos

Thrust: vacuum

3,56 tf

The engine is designed to be reused during several missions

PAYLOAD FAIRING

Specific impulse: sea level

294,8 Isp

Specific impulse: vacuum

346,8 Isp

SR ROCKETs

Nebo

SPECIFICATIONS

Suborbital launch vehicle

Commercial single-stage suborbital launch vehicle designed for several scientific missions such as meteorological research and testing various systems at altitudes up to 120 km

Payload to 120 km LEO

20 kg

Specifications

Nebo

FIRST STAGE

Launch mass

Length

0,5 t

6,9 m

Diameter

0,45 m

Propellants

First stage length

oxygen and methane

4,3 m

Target launch cost

335 ths $

Nebo

SPECIFICATIONS

First stage

First stage length

4,3 m

Nebo

RD-1 liquid propellant rocket engine. Propellants: oxygen, methane

PAYLOAD FAIRING

Thrust: sea level

0,86 tf

Thrust: vacuum

1,02 tf

Specific impulse: sea level

294,8 Isp

Specific impulse: vacuum

346,8 Isp

FIRST STAGE

ENGINE

Payload fairing

The payload fairing is built from a composite material produced by SR Space

Nebo

Payload fairing diameter

0,45 m

Payload fairing length

1,9 m

Engine

Nebo

PAYLOAD FAIRING

The RD-1 liquid-propellant rocket engine is built according to the open cycle layout. Oxygen and methane are used as propellant. The engine is designed to be reused during several missions

Thrust: sea level

0,86 tf

Thrust: vacuum

1,02 tf

Specific impulse: sea level

294,8 Isp

Specific impulse: vacuum

346,8 Isp

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SR ROCKETs

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