RD-0120 (rocket engine) | Wikipedia audio article
Channel: wikipedia tts
Date: 2019-05-17

This is an audio version of the Wikipedia Article:
https://en.wikipedia.org/wiki/RD-0120


00:01:28 1 Specifications
00:01:38 1.1 RD-0120
00:02:35 2 See also



Listening is a more natural way of learning, when compared to reading. Written language only began at around 3200 BC, but spoken language has existed long ago.

Learning by listening is a great way to:
- increases imagination and understanding
- improves your listening skills
- improves your own spoken accent
- learn while on the move
- reduce eye strain

Now learn the vast amount of general knowledge available on Wikipedia through audio (audio article). You could even learn subconsciously by playing the audio while you are sleeping! If you are planning to listen a lot, you could try using a bone conduction headphone, or a standard speaker instead of an earphone.

Listen on Google Assistant through Extra Audio:
https://assistant.google.com/services/invoke/uid/0000001a130b3f91
Other Wikipedia audio articles at:
https://www.youtube.com/results?search_query=wikipedia+tts
Upload your own Wikipedia articles through:
https://github.com/nodef/wikipedia-tts
Speaking Rate: 0.8450110722254771
Voice name: en-US-Wavenet-D


"I cannot teach anybody anything, I can only make them think."
- Socrates


SUMMARY
=======
The Soviet RD-0120 (also designated 11D122) was the Energia core rocket engine, fueled by LH2/LOX, roughly equivalent to the Space Shuttle Main Engine (SSME). These were attached to the Energia core rather than the orbiter, so were not recoverable after a flight, but created a more modular design (the Energia core could be used for a variety of missions besides launching the shuttle). Baselined from the more mature American hydrogen–oxygen engine technology, but considerably modified with Russian innovations and methods, the RD-0120 and the SSME have both similarities and differences. The RD-0120 achieved nearly identical specific impulse and combustion chamber pressure with reduced complexity and cost, as compared to the SSME, primarily at the expense of lower thrust-to-weight ratio. It uses fuel-rich staged combustion cycle and a single shaft to drive both the fuel and oxidizer turbopumps. Some of the Russian design features, such as the simpler and cheaper channel wall nozzles, were evaluated by Rocketdyne for possible upgrades to the SSME. It achieved combustion stability without the acoustic resonance chambers that the SSME required.