The test bench equipment allows performing:
- firing tests of liquid rocket engines (LRE), their components (combustion chambers, turbopump units, gas generators et al.);
- firing tests of liquid propulsion systems (LPS) in a low pressure chamber;
- firing tests of liquid thrusters (LT).
The tests are conducted on propellants – unsymmetrical dymethylhydrazine and nitrogen tetroxide.
The following is ensured:
- simulation of full-scale conditions during tests;
- automated parameters recording and testing control;
- reliability of technological equipment;
- effective purification of hazardous emissions;
- neutralization of tested units after tests.
Basic Technical Characteristics
|
|
LRE |
LPS |
LT |
|
Thrust, tup to 1 |
up to 1 |
up to 0.1 |
up to 0.01 |
|
Propellants supply pressure, kgf/cm2 |
up to 200 |
up to 20 |
up to 40 |
|
Propellants thermostating, °С |
0…+50 |
+10…+35 |
- |
|
Hardware thermostating, °С |
|
+25…+35 |
|
|
Gas pickup (degassing) |
to specified values | ||
|
Simulation of full-scale conditions at nozzle section, kgf/cm2 |
~0,004..0,008 |
~0,014…0,2 |
~0,004…0,13 |
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