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RDMT engine series

Original archive entry. The text, images and links below are kept as they were written.

Subtopics

  • RDMT-2600 NII Mash GOX/Alcohol rocket engine. Developed 1980's. Experimental low-thrust thruster.
  • RDMT-400A NII Mash N2O4/UDMH rocket engine. Developed 1980's. Experimental low-thrust thruster. Niobium combustion chamber with coating.
  • RDMT-400 X NII Mash N2O4/UDMH rocket engine. Developed 1980's. Experimental low-thrust thruster. Carbon combustion chamber. Mass may be chamber only.
  • RDMT-8 X NII Mash N2O4/UDMH rocket engine. Developed 1980's. Experimental low-thrust thruster.
  • NII 612 kgf NII Mash N2O4/UDMH rocket engine. experimental 612.25 kgf / 0.071 metric tons thrust / 0.031tf. Developed. Experimental thruster, 3 thrust levels by 4 valves: 6000 N, 0.7 N, 0.3 N. Specific impulse 326 - 286 sec.
  • RDMT-100 NII Mash N2O4/UDMH rocket engine. Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites. In Production. Low-thrust attitude control thruster.
  • RDMT-200 NII Mash N2O4/UDMH rocket engine. Almaz. In Production. Low-thrust attitude control thruster.
  • RDMT-400 NII Mash N2O4/UDMH rocket engine. Almaz, Kvant, Kristall, Spektr, Priroda. In Production. Low-thrust attitude control thruster. Used in Isayev 11D458 engine.
  • RDMT-50 NII Mash N2O4/UDMH rocket engine. Kosmos satellites. In Production. Low-thrust attitude control thruster.
  • RDMT-12 Isayev / NII Mash N2O4/UDMH 12-13 N low-thrust attitude control thruster. Used on Almaz, Kvant, Kristall, Spektr, and Priroda spacecraft; and in Briz and Briz-M upper stages. In Production. Predecessor was RDMT-400. Thrust given as 0.0133 N / Isp = 247 and 270 sec in S5.98M Briz, Briz-M upper stage application.
  • RDMT-135 NII Mash N2O4/UDMH rocket engine. Salyut, Mir, Soyuz-T and -TM, Progress, Kosmos-satellites. In Production. Low-thrust attitude control thruster.
  • RDMT-5 Null
  • RDMT-200K NII Mash GOX/Kerosene rocket engine. Buran. Out of Production. Low-thrust attitude control thruster. Mass in ref. NIIMash 95 given as only 2.5 kg.
  • RDMT-0.4 X NII Mash N2O4/UDMH rocket engine. In Production. Experimental low-thrust thruster. Chamber from niobium alloy. Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec.