China's Space Program Thread II

[by78]

In a major milestone, Zhongke/CAS Space has successfully carried out a static test fire of Lijian-2's first stage.

Only two weeks after the 1st-stage static fire test, Zhongke/CAS successfully carried out the static test fire of Lijian-2's 2nd-stage propulsion system, during which the engine was successfully restarted.

 

[GulfLander]

I assume this is for space(?)
China's Northwest Poly. Univ tested "Flying 2" (Hypersonic vehicle(?))

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[Asug]

I assume this is for space(?)
China's Northwest Poly. Univ tested "Flying 2" (Hypersonic vehicle(?))

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Possibly, but not necessarily. As far as I understand, hypersonic vehicles are being developed, and Feitian-1 (2022) and Feitian-2 are "flying test stand".

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[eric7]

I assume this is for space(?)
China's Northwest Poly. Univ tested "Flying 2" (Hypersonic vehicle(?))

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It's an experimental aircraft for Rocket-Based Combined Cycle, RBCC, a tech for space plane or SSTO

 

[escobar]

Overview of current progress of the upcoming RLV

 

[by78]

An update on Zhuque-3 launch vehicle. Zhang Jinru, VP of LandSpace re-confirmed that the maiden launch of Zhuque-3 will take place in the 2nd half of this year (sometime in Q3). The company also expects to conduct a launch and 1st-stage recovery by the end of this year.

The first flight of Zhuque-3 has been pushed back slightly, from Q3 to Q4.

 

[by78]

Yet another launch startup has joined the crowded race. Weiguang (微光启航) has introduced its two-stage resuable WG-1 launch vehicle. Brief specs are below.

– All carbon fiber composite construction: both body and tanks
– Diameter: 3.8m
– Length: 60m
– Take-off mass: 350 tons
– Capacity to LEO: ≥11 tons (single use), ≥9 tons (reusable)
– Capacity to SSO: ≥9 tons (single use), ≥7 tons (reusable)
– 1st stage: powered by 11 Huaguang-1 (华光一号) LOX/Methane (full-flow staged combustion cycle) engines, each producing 42 tons of thrust at sea level)
– 2nd stage: powered by a single Huaguang-1 vaccum engine, thrust of 52 tons

 

[AndrewJ]

F9FT can send 14,460kg to 51.6 degree inclination 400km circular LEO (ISS orbit) using ASDS landing (1), with launch mass 549t. That gives a payload mass fraction of 2.63%. CZ-10A's payload mass figure for LEO can't be referring to a worse LEO orbit than that. CZ-10A's barge landing payload is 14t, with a launch mass of 750t. This gives a payload mass fraction of 1.87%. So F9FT has a payload mass fraction that is 41% higher. This is despite CZ-10A benefiting from scale, staged combustion, and the elimination of landing legs. There seems to be something very suboptimal with the design. The choice to eliminate landing legs and use unproven wire-catching instead, while innovative, raises the suspicion that 14t is indeed the absolute limit, and that CZ-10A wouldn't be able to send the new crewed spacecraft to the space station if it had conventional landing legs.

Any updates on these params? The initial payload efficiency is not that good.

 

[gelgoog]

Falcon 9 has a really lightweight airframe with Al-Li alloys and really thin tanks. My guess is CZ-10 uses much heavier isogrid construction methods similar to US EELV rockets.

I agree that ditching the landing legs is a bad idea.

CZ-10 design is a compromise where they design a reusable rocket using available building blocks. This means they can get the rocket out faster and cheaper. The penalty is slightly suboptimal performance.

Long term they can probably increase engine thrust or something to get some performance back.

 

[by78]

The Shenzhou-20 has conducted a second spacewalk. It lasted 6 hours and 30 minutes, during which additional space debris protection was installed on the exterior of the space station. The taikonauts also installed additional equipment that will improve the efficiency of future spacewalks and help shorten them by 40 minutes.