China's Space Program Thread II

taxiya

Brigadier
Registered Member
Six newly published articles on the various systems and operational aspects of the Chinese space station. I'm sure they make some very interesting read. @taxiya

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A quick reading of the manipulator, I find this table interesting
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It is a comparison between SSRMS (canada arm) and CSS arm. There was a discussion among fans about the maximum load of the arms. The question was why SSRMS can take much higher load. From this table, it seems to me that there is no difference.

The green figures are similar between the two, the rigidities means that both arms are equally strong before they are bent and damaged. The maximum radial angular velocity indicate that they may have similar acceleration if their tasks should take similar amount of time. This also means that the motor's torque is about the same (not stated in the table).

The only difference related to load is the maximum linear velocity. SSRMS's lowest velocity is in a range lower than CSS arm, maximum ratio is 4.16/1 (CSS/SSRMS). Assuming the torque is similar (see above), it means that SSRMS has chosen to have a much lower acceleration which limits its top working speed before the arm is fully extended or folded. Same force gives higher mass a lower acceleration, or lower mass but higher acceleration. If we reduce the top working linear velocity of CSS arm to 1/4.16th, we would get 104t which is on the same level as SSRMS.

Notice that rigidities of JEMRMS (Japan arm) and ERA (Europe arm) are 1/10 of SSRMS and CSS arm, meaning they can only move a much lower mass to the same distance within the same time for a similar task.

What is outstanding is that the mass of CSS arm is on the same level as ERA and JEMRMS, but its rigidity is 10 times of them, I wonder why.
 
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Andy1974

Senior Member
Registered Member
Six newly published articles on the various systems and operational aspects of the Chinese space station. I'm sure they make some very interesting read. @taxiya

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This will help set standards.
 

iantsai

Junior Member
Registered Member
2022年9月25日6时55分,我国在太原卫星发射中心使用快舟一号甲运载火箭,以“一箭双星”方式,成功将试验十四号和试验十五号卫星发射升空,卫星顺利进入预定轨道,发射任务取得圆满成功。

试验十四号卫星主要用于开展科学试验、新技术验证等领域,试验十五号卫星主要用于国土普查、城市规划和防灾减灾等领域。

此次任务是快舟一号甲运载火箭第18次飞行,也是该型火箭2022年第4次执行发射任务。
China launched Shiyan-14 and Shiyan-15 experiment satelites by a KZ-1 rocket from Taiyuan Satelite Launch Center in 06:55 UTC+8, Sept 25, 2022.

Shiyan-14 is a science experimental satelite to verify new technologies. Shiyan-15 is purposed for land survey, metropolitan planning and disaster prevention and mitigations.

This is the 18th mission of KZ-1 series rockets, and also 4th mission of the year.
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by78

General
China launched Shiyan-14 and Shiyan-15 experiment satelites by a KZ-1 rocket from Taiyuan Satelite Launch Center in 06:55 UTC+8, Sept 25, 2022.

Shiyan-14 is a science experimental satelite to verify new technologies. Shiyan-15 is purposed for land survey, metropolitan planning and disaster prevention and mitigations.

This is the 18th mission of KZ-1 series rockets, and also 4th mission of the year.

High-resolution images.

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by78

General
Some presentation slides on CASIC's single-stage-to-orbit (SSTO) spaceplane project.

The project will study and explore several configuration schemes (ranging from 100-ton to 640-ton takeoff weight) and their associated power requirements, carry out verifications of the Yunlong engine, and study and nail down the real-world requirements for SSTO spaceplane. A special emphasis will be paid to the 240-ton and 480-ton configurations, which are expected to require two and four Yunlong engines (60-ton thrust), respectively. The project aims to realize the capability to launch 7.7 to 19.2-ton to LEO, which will cover most of China's satellite launch needs as well as manned and cargo missions to the Chinese space station.

Much progress has been made on the 480-ton takeoff configuration, including aerodynamic design and parameters such as dimensions and mass distribution. The length of the spaceplane is 95.6m, wingspan is 30m, the fuselage slenderness ratio is 13.9, and the total fuselage volume is 2779.6 cubic meters, of which 1861.7 cubic meters are dedicated to propellant (67% of the total volume).

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