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Bipropellant low thrust rocket engine РДМТ12
Bipropellant low thrust rocket engine
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Description |
The thruster is designed to move a space vehicle (SV) in the space by commands, provided by the control system (CS). The thruster produces the rated thrust of 13.3 N value and it is capable for the
repeated starts-up of duration from 0.03 sec to 10,000 sec.
In the thruster there is a solenoid-operated valve (SOV) of 12PT.200.00 type, developed and fabricated by R&DIME. The SOV is a single-seat, single-stage valve with the teflon sealing and is designed for supply and shut-off of propellant components for injector. The valve has a mass of 0.035 kg, a response time of not over 0.015 sec, a current consumption of not over 0.083 A at the 34 V voltage and 20C temperature. The thruster has the flow rate stabilizers of fuel and oxidizer ensuring the constant flow rate of components at possible changes of pressure at the inlet. It permits to limit the range of thrust change within 13.0...14.0 N at the fluctuation of inlet pressure from 1.18 to 3.43 MPa. The chamber and nozzle of thruster are manufactured from stainless steel.
At the delivery of voltage to the SOV contacts by command from CS the valves are opened. The propellant components via the passages of injector enter the combustion chamber, where the setf-ignition of propellant and its combustion take place. The combustion products, out flowing through the nozzle, produce thrust of thruster. The thruster is cut off be removing voltage from the valve`s contacts and in this case the valves are closed, and the access of components to the combustion chamber stops. The duration of thruster`s run and pauses between its starts-up is regulated by CS. The thruster to be
supplied for customer doesn`t require adjustment and regulation.
The thermal condition of thruster during its operation in all the modes is provided by external regenerative cooling of combustion chamber and radiation cooling of nozzle. The oxidizer and fuel, entering the thruster, at first go through the cooling passage, made in a form of tubes wound on the combustion chamber, then through SOV enter the combustion chamber. The thermal condition of thruster within passive life in space is controlled by a temperature sensor, installed in the area of oxidizer valve. The required level of temperature in order to exclude freezing of oxidizer is provided by turning-on the electric heaters with the power not over 2 W at the supply voltage of 27 V. If required it is possible to keep the temperature regime by a contract heat transfer via the flange of thruster attachment to SV.
The combination of methods for thermal condition providing is possible.
To the beginning of 2001 149 pcs of such type thruster have been operationally used in the ”ALMAZ” orbital station, in booster unit ”BRIZ”, in the ”MIR” orbital station augmentation modules ”KVANT”,
”KVANT-2”, ”KRISTALL”, ”SPEKTR”, ”PRIRODA”, and in the first Russian module ”ZARYA” of International Space Station (ISS).
R&DIME possesses the stand, experimental, production bases, the scientific, engineering and designing potential, allowing to carry out scientific and research works and experimental-designing works on production of small-class engine in all the directions in interests of domestic and foreign companies. R&DIME conclude contracts on series-produced Low Thrust Rocket Engines and electrically actuated valves production and supply.
R&DIME offers to perform tests of large scale systems and technologies and also up to 3,OOOkN sustainer liquid rocket engines themselves and units of their supply systems with the LO,+LH2 (L methane) propellants.
R&DIME possesses the stand, experimental, production bases, the scientific, engineering and designing potential, allowing to carry out scientific and research works and experimental-designing works on production of small-class engine in all the directions in interests of domestic and foreign companies. R&DIME conclude contracts on series-produced Low Thrust Rocket Engines and electrically actuated valves production and supply.
R&DIME offers to perform tests of large scale systems and technologies and also up to 3,OOOkN sustainer liquid rocket engines themselves and units of their supply systems with the LO,+LH2 (L methane) propellants.
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