Production

25
 2018

Rocket engines, designed by Turaevo Machine-building Design Bureau “SOYUZ”.

Principal specifications of dual–component low thrust liquid rocket engines.

Specifications

Engine identifications

МДТО-123

МДТО-123-01

МДТО-121

1

Engine thrust in steady state in a vacuum, kg

10

5

2.5

2

Specific thrust (no less than), kgf/kg sec

260

260

245

3

Fuel components ratio

1.85

1.85

1.85

4

Fuel components:

- oxidizer

- fuel

 

N2O4

UDMH

 

N2O4

UDMH

 

N2O4

UDMH

5

Total fuel consumption, g/sec

36

18.2

9.8

6

Burns total number (no less than)

250000

250000

250000

7

Total fire run time, sec

3000

3000

3000

8

Single burn maximal time, sec

700

700

700

9

Guaranteed occurring of propulsive burn with valve power supply voltage from 22 to 34V, sec

 

0,06

 

0,06

 

0,06

10

Engine firing maximal frequency in impulse mode, hz

 

7

 

7

 

7

11

Build-up time to steady thrust, sec

0,1

0,1

0,1

12

Current of engine’s valve magnet coil, A:

 - at 27V current and 20°С temperature;

- at 34V current and minus 3°С temperature

 

0,91

1,27

 

0,91

1,27

 

0,91

1,27

13

Inductor of valve’s magnet coil, henry

1,4

1,4

1,4

14

Engine weight (no more than), kg

1,1

1,1

1,0

15

Engine’s inlet fuel pressure,  kgf/cm2

10…32

10…32

10…32

These engines are designed to orientate, stabilize and create spacecraft axial overload. Engines specifications are shown under the inlet fuel pressure in 15 kgf/cm2.

 

Principal specifications of dual –component low thrust liquid rocket engines.

Specifications

Engine identifications

МДТО-117

МДТО-118

МДТО-199

1

Engine thrust in steady state in a vacuum, kg

0,04

0,3

0,6

2

Specific thrust (no less than),

200

220

230

3

Fuel components ratio

1.85

1.85

1.85

4

Fuel components:

- oxidizer

- fuel

 

N2O4

UDMH

 

N2O4

UDMH

 

N2O4

UDMH

5

Total fuel consumption, g/sec

 

 

 

6

Burns total number (no less than), kgf/kg sec

100000

250000

250000

7

Total fire run time, sec

345600

3000

3000

8

Single burn maximal time, sec

345600

300

300

9

Guaranteed occurring of propulsive burn with valve power supply voltage from 22 to 34V, sec

 

0,1

 

0,06

 

0,06

10

Engine firing maximal frequency in impulse mode, hz

 

7

 

7

 

7

11

Current of engine’s valve magnet coil, A:

 - at 27V current and 20°С temperature;

- at 34V current and minus 3°С temperature

 

0,91

1,27

 

0,91

1,27

 

0,91

1,27

12

Inductor of valve’s magnet coil, henry

1,4

1,4

1,4

13

Engine weight (no more than), kg

1,3

1,0

1,0

14

Engine’s inlet fuel pressure,  kgf/cm2

5,5…6,5

10…32

10…32

These engines are designed to orientate, stabilize and adjust spacecraft orbits. The specifications is given with inlet fuel pressure:

-  For МД-10 118 and МД-ТО 199 engines – 15 kgf/cm2;

- For МД-ТО 117 – 6 kgf/cm2.