by78
General
Here is the nozzle, or part of it.
An autoclave(?) used in the fabrication of the nozzle:
China's Space Program News Thread
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Here is the nozzle, or part of it.
An autoclave(?) used in the fabrication of the nozzle:
an add on from @by78 postHere is the nozzle, or part of it.
An autoclave(?) used in the fabrication of the nozzle:
from CnTechPost
China's latest breakthrough lays foundation for heavy-lift launch vehicle development
March 20, 2021A Chinese state-owned conglomerate has successfully developed the country's first 2.5-meter diameter class of heavy-duty hydrogen-oxygen engine nozzles, laying the foundation for the development of heavy-lift launch vehicles.
The China Aerospace Science and Technology Corporation (CASC), the nation's leading space contractor, on March 19 , achieved by its Plant 211, saying it marks the first time its diffusion brazing technology capability for large stainless steel components has reached the world's advanced level.
The largest and most visible part of a rocket engine is the huge nozzle, whose main function is to convert the heat energy of the high-temperature, high-pressure gas produced by the rocket's propellant fuel into kinetic energy, thus giving the rocket a huge thrust.
(Preparing the 2.5-meter diameter regenerative cooling nozzle before entering the furnace.)
The CASC's engine nozzle is divided into two sections, the upper section with a maximum diameter of 1.8 meters and the lower section with a maximum diameter of 2.5 meters.
It has a wall thickness of just 1 mm at its thinnest point and is manufactured using a diffusion brazing process with a milled inner wall and a direct overlay structure on the outer wall, the CASC said.
In this breakthrough, the CASC overcame technical problems including structural design technology of diffusion brazing process for large-size parts, matching of the high and low temperature of tooling, and control of brazing deformation of large-size parts.
Currently, China's most powerful rocket is the Long March 5, which has a near-Earth orbit capacity of 25 tons.
In order to meet the needs of future deep space exploration and lunar exploration projects, China needs to develop a brand-new launch vehicle.
Previously, Luan Enjie, an academician of the Chinese Academy of Engineering and the first chief director of China's lunar exploration project, said in a media interview that China will develop a 100-ton heavy launch vehicle in the future to meet the demand for going deeper into space.
At present, the demonstration stage of China's heavy launch vehicle has been basically completed, entering the follow-up stage of the project, its research work is expected to be launched during the 14th Five-Year Plan.
(The 2.5m diameter regenerative cooling nozzle after welding.)
Jilin-1 satellite tracking aircraft speed at Atlanta Airport.
Now someone tell me that you can't track carriers in open ocean
New photo of Mars taken by Tianwen.
Hendrik_2000
Lieutenant General
Amazing picture taken by tianwen
A recent picture circulating (the last picture) seems to tell the CZ-9's latest payload figures: LEO 180t and LTO 65t. For comparison the largest Ares V configuration (LV51.00.48) was LEO 187.7t and LTO (TLI) 62.8t.
The final SLS block II cargo is LEO 130t and LTO 45t. As can been seen SLS is not proper comparison with CZ-9. I say this because very often some members bring up SLS when talking about design rational behind CZ-9. However in reality CZ-9 is in the same class of Ares V in terms of the mission capability therefor shares the same rational with Ares V. SLS on the other hand is quite different philosophy and purpose.
Here is the progression of CZ-9 concept design:
The very early design, length: 93 meters, LEO 140t and LTO 50t, the 2nd stage engine is open circle (gas generator)
Then the 2nd stage engine is changed to close circle (staged combustion) and length grow to 103 meters, that is 10 meters longer meaning more fuel with a more efficient 2nd stage therefor more payload. But I did not find the corresponding ppt showing the new LEO payload figure. Strangely the LTO payload is 50t unchanged. I regard it as a mistake.
Here is a picture showed up very recently in the last month, just after the announcement of CZ-9 program. Note, there is no CASC logo with it. So I can't be sure of its authenticity. But considering the improved 2nd stage engine and increased fuel volume, the payload figures seem very reasonable. LEO 180t and LTO 65t.
Another interesting thing is the CZ-9B variant. There are four YF-130 engines arranged in a way that the twin nozzles in a cross shape. In the middle, there are two smaller nozzles. It is either that the two nozzles are of another YF-130 and the ppt is not in right proportion, or they belongs to two smaller engines (YF-100).
The final SLS block II cargo is LEO 130t and LTO 45t. As can been seen SLS is not proper comparison with CZ-9. I say this because very often some members bring up SLS when talking about design rational behind CZ-9. However in reality CZ-9 is in the same class of Ares V in terms of the mission capability therefor shares the same rational with Ares V. SLS on the other hand is quite different philosophy and purpose.
Here is the progression of CZ-9 concept design:
The very early design, length: 93 meters, LEO 140t and LTO 50t, the 2nd stage engine is open circle (gas generator)
Then the 2nd stage engine is changed to close circle (staged combustion) and length grow to 103 meters, that is 10 meters longer meaning more fuel with a more efficient 2nd stage therefor more payload. But I did not find the corresponding ppt showing the new LEO payload figure. Strangely the LTO payload is 50t unchanged. I regard it as a mistake.
Here is a picture showed up very recently in the last month, just after the announcement of CZ-9 program. Note, there is no CASC logo with it. So I can't be sure of its authenticity. But considering the improved 2nd stage engine and increased fuel volume, the payload figures seem very reasonable. LEO 180t and LTO 65t.
Another interesting thing is the CZ-9B variant. There are four YF-130 engines arranged in a way that the twin nozzles in a cross shape. In the middle, there are two smaller nozzles. It is either that the two nozzles are of another YF-130 and the ppt is not in right proportion, or they belongs to two smaller engines (YF-100).
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eeeeh??! I thought it deorbited in 2019 not 2021!
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