The RD-0110R (Russian: Ракетный Двигатель-0110R, romanized: Raketnyy Dvigatel-0110R, lit. 'Rocket Engine 0110R', GRAU index: 14D24) was a rocket engine burning kerosene in liquid oxygen in a gas generator combustion cycle. It had four nozzles that can gimbal up to 45 degrees in a single axis and was used as the vernier thruster on the Soyuz-2.1v first stage.[1] It also had heat exchangers that heat oxygen and helium to pressurize the LOX and RG-1 tanks of the Soyuz-2.1v first stage, respectively. The oxygen was supplied from the same LOX tank in liquid form, while the helium was supplied from separate high pressure bottles (known as the T tank).[1]

The engine's development started in 2010 and it is a heavily modified version of the RD-0110. The main areas of work were shortening the nozzles to optimize them for the atmospheric part of the flight (the RD-0110 is a vacuum optimized engine), propellant piping, heat exchangers and the gimballing system, which was developed by RKTs Progress. The RD-0110R engine was produced at the Voronezh Mechanical Plant.[2]

See also

  • Soyuz-2-1v - The first rocket to use the RD-0110R
  • KBKhA - The RD-0110R designer bureau
  • RSC Progress - The designer of the Soyuz-2.1v and the RD-0110R nozzle gimbal
  • Voronezh Mechanical Plant - A space hardware manufacturer company that manufactures the RD-0110R

References

  1. ^ a b c d e f g h i j k l m n o p q "Steering engine RD0110R (14D24). Carrier rocket "Soyuz-2-1v"" (in Russian). KBKhA. Archived from the original on 11 August 2013.
  2. ^ a b c Zak, Anatoly. "RD-0110R". russianspaceweb.com. Retrieved 2015-06-01.
Allikas: http://en.wikipedia.org/wiki/RD-0110R
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