To install click the Add extension button. That's it.

The source code for the WIKI 2 extension is being checked by specialists of the Mozilla Foundation, Google, and Apple. You could also do it yourself at any point in time.

How to transfigure the Wikipedia

Would you like Wikipedia to always look as professional and up-to-date? We have created a browser extension. It will enhance any encyclopedic page you visit with the magic of the WIKI 2 technology.

Try it — you can delete it anytime.

Install in 5 seconds
4,5
Kelly Slayton
Congratulations on this excellent venture… what a great idea!
Alexander Grigorievskiy
I use WIKI 2 every day and almost forgot how the original Wikipedia looks like.
Live Statistics
English Articles
Improved in 24 Hours
Added in 24 Hours
Languages
Recent
Show all languages
What we do. Every page goes through several hundred of perfecting techniques; in live mode. Quite the same Wikipedia. Just better.
Great Wikipedia has got greater.
.
Leo
Newton
Brights
Milds

RD-0110R

From Wikipedia, the free encyclopedia

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 originRussia
First flight2013-12-28
DesignerKBKhA,[1] Viktor Gorokhov[2]
ManufacturerVoronezh Mechanical Plant[2]
Application1st stage vernier engine
Associated LVSoyuz-2-1v[1]
PredecessorRD-0110[1]
StatusIn Production
Liquid-fuel engine
PropellantLOX[1] / RG-1[1]
CycleGas Generator[1]
Configuration
Chamber4[1]
Performance
Thrust, vacuum265.1 kilonewtons (59,600 lbf)[1]
Thrust, sea-level230.5 kilonewtons (51,800 lbf)[1]
Chamber pressure6.6 megapascals (960 psi)[1]
Specific impulse, vacuum298.4 seconds[1]
Specific impulse, sea-level259.4 seconds[1]
Burn time210s[1]
Dimensions
Length1,910 millimetres (75 in)[1]
Diameter2,675 millimetres (105.3 in)[1]
Dry weight850 kilograms (1,870 lb)[1] (including the support ring)
Used in
Soyuz-2-1v first stage.

The RD-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]

See also

References

  1. ^ a b c d e f g h i j k l m n o p q r "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.

External links

Stub icon

This rocketry article is a stub. You can help Wikipedia by expanding it.

This page was last edited on 24 July 2023, at 01:59
Basis of this page is in Wikipedia. Text is available under the CC BY-SA 3.0 Unported License. Non-text media are available under their specified licenses. Wikipedia® is a registered trademark of the Wikimedia Foundation, Inc. WIKI 2 is an independent company and has no affiliation with Wikimedia Foundation.
Contact WIKI 2
Introduction
Terms of Service
Privacy Policy