RD-0110R

RD-0110R
	The four nozzles of the RD-0110R surround the large single nozzle of the NK-33 engine on the first stage of the Soyuz-2-1v.
Country of origin	Russia
First flight	2013-12-28
Designer	KBKhA, Viktor Gorokhov
Manufacturer	Voronezh Mechanical Plant
Application	1st stage vernier engine
Associated LV	Soyuz-2-1v
Predecessor	RD-0110
Status	In Production
Liquid-fuel engine
Propellant	LOX / RG-1
Cycle	Gas Generator
Configuration
Chamber	4
Performance
Thrust, vacuum	265.1 kilonewtons (59,600 lbf)
Thrust, sea-level	230.5 kilonewtons (51,800 lbf)
Chamber pressure	6.6 megapascals (960 psi)
Specific impulse, vacuum	298.4 seconds
Specific impulse, sea-level	259.4 seconds
Burn time	210s
Dimensions
Length	1,910 millimetres (75 in)
Diameter	2,675 millimetres (105.3 in)
Dry mass	850 kilograms (1,870 lb) (including the support ring)
Used in
	Soyuz-2-1v first stage.

The RD-0110R (Russian: Ракетный Двигатель-0110R, romanized: Raketnyy Dvigatel-0110R, lit. 'Rocket Engine 0110R', GRAU index: 14D24) is a rocket engine burning kerosene in liquid oxygen in a gas generator combustion cycle. It has four nozzles that can gimbal up to 45 degrees in a single axis and is used as the vernier thruster on the Soyuz-2-1v first stage.^[1] It also has 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 is supplied from the same LOX tank in liquid form, while the helium is 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 TsSKB Progress. The RD-0110R engine is produced at the Voronezh Mechanical Plant.^[2]