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 MAKS 2005 - International Aviation & Space Salon
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Bipropellant low thrust rocket engine РДМТ 100А

Bipropellant low thrust rocket engine
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Photo Description
The thruster is designed to move a space vehicle (SV) in the space by commands, provided by the control system (CS). thruster produces the rated thrust of 98 N value and it is capable for the repeated starts-up of duration from 0.03 sec to 3,000 sec. РДМТ100А thruster is created basing on РДМТ50М design with maximum utilizing developed units.
In the thruster there is a solenoid-operated valve (SOV) of PT.200.00-02 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 propellant components for injector. The valve has a mass of 0.18 kg, a response time of not over 0.03 sec, a current consumption of not over 0.45 A at the voltage 34 V and temperature 20C. The inlet pipelines of oxidizer and fuel are welded to the valves. The trim orifices for adjustment of flow rate of oxidizer and fuel are installed inside the above pipelines. With the help of trim orifices the thruster is adjusted to the preset mixture ratio. The chamber and nozzle of thruster are manufactured from combustion alloy with heat-resistant silicate coating.
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 self-ignition of propellant and its combustion take place. The combustion products, outlawing through the nozzle, produce thrust of thruster. The thruster is cut off by 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 internal Him cooling of combustion chamber and radiation cooling of nozzle. The thermal condition of thruster within passive life in the 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 way of turning-on two electric heaters of total power not over 2.5 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. A thermal shield of nozzle can be install in order to reduce heat radiation fluxes from nozzle to elements of SV located in proximity to the working thruster.
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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Cool gas low thrust rocket engine
МД5
РДМТ08
Gas-Dynamic Igniter
ГДВВВ-185
Gas-Dynamic Igniters
Bipropellant low thrust rocket engine
РАМТ135А
PAMT500A/I
РДМТ12
РДМТ 50М
РДМТ 100А
РДМТ 135М
РДМТ 200 К
РДМТ 200А
РДМТ 200М
Reactive Control System Module
Reactive Control System Module
Cutter for thermal cutting of materials
100ЭР568.49
100ЭР568.55
Mass Flow Rate Stabilizers
Mass Flow Rate Stabilizers
Solenoid Valves for Engineering Industry
Solenoid Valves for Engineering Industry
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El: 77-6097 from 14 February 2002. Publishes since February, 3, 1997.