Production
|
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.
|
Русский
