Author Topic: Landspace - ZhuQue-3 (ZQ-3) launcher (Read 66618 times)

FutureSpaceTourist · « **on:** 11/21/2023 05:32 am »

https://twitter.com/cnspaceflight/status/1726812640876564968

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👀 Introducing Zhuque-3
Keywords: reusable, methane, stainless steel, 20t expended, >16.5t landing on ship, >11t landing on land, 9 TQ-12A engines (?)
Source: https://weibo.com/6065432153/4970458732303379

FutureSpaceTourist · « **Reply #1 on:** 11/25/2023 07:54 pm »

https://twitter.com/124970mev/status/1728509650461495755

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As Landspace prepares for the third flight of its ZhuQue-2 rocket, it announced a significantly larger stainless steel vehicle. @BCCarCounters has the details for @NASASpaceflight:

https://www.nasaspaceflight.com/2023/11/china-roundup/

Galactic Penguin SST · « **Reply #2 on:** 12/09/2023 01:30 am »

https://twitter.com/CNSpaceflight/status/1733299361428488470

https://twitter.com/Cosmic_Penguin/status/1733312519748673634

FutureSpaceTourist · « **Reply #3 on:** 12/09/2023 03:50 am »

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👀 Introducing stainless steel methane "Falcon-9" - Zhuque-3
¥20,000RMB/kg (~$2,800USD/kg)

https://twitter.com/cnspaceflight/status/1733326217699635211

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Weibo post says LANDSPACE plans to do a VTVL hop test soon
weibo.com/5549194014/497…

FutureSpaceTourist · « **Reply #4 on:** 12/09/2023 04:24 am »

twitter.com/cnspaceflight/status/1733356076152795234

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One more animation of Zhuque-3 reveals more design details.
The second stage engine TQ-15B will produce 1183kN thrust in vacuum with 3500s specific impulse

Edit to add:

https://twitter.com/cnspaceflight/status/1733356918742376709

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Designed to be like Falcon-9 and designed to launch things like being launched by Falcon-9, but stainless steel and methane

jdon759 · « **Reply #5 on:** 12/09/2023 04:39 am »

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One more animation of Zhuque-3 reveals more design details.
The second stage engine TQ-15B will produce 1183kN thrust in vacuum with 3500s specific impulse

3500s Isp? That sounds optimistic.

Steven Pietrobon · « **Reply #6 on:** 12/09/2023 04:48 am »

Quote from: jdon759 on 12/09/2023 04:39 am

3500s Isp? That sounds optimistic.

It's 3500 m/s or 356.9 s.

jdon759 · « **Reply #7 on:** 12/09/2023 04:50 am »

Ahh, makes sense. Screen too small to see detail in that video, so was just going off the tweet text

FutureSpaceTourist · « **Reply #8 on:** 12/09/2023 05:12 am »

https://twitter.com/cnspaceflight/status/1733368808486940815

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sorry for the typo, 3500m/s

FutureSpaceTourist · « **Reply #9 on:** 12/09/2023 05:26 am »

https://twitter.com/raz_liu/status/1733355671402491979

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According to the CEO of landscape. They will do a VTVL test in next 20ish days. Via mbd.baidu.com/newspage/data/…

FutureSpaceTourist · « **Reply #10 on:** 12/09/2023 10:42 am »

https://twitter.com/raz_liu/status/1733443549499412895

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3D rendering of Zhuque-3

FutureSpaceTourist · « **Reply #11 on:** 12/10/2023 08:00 am »

https://twitter.com/raz_liu/status/1733705611098177891

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Land Space VTVL test launch pad & demonstration pics. Rumors say the test will happen in next week. via m.weibo.cn/status/4977361…

FutureSpaceTourist · « **Reply #12 on:** 12/10/2023 08:37 am »

https://twitter.com/cnspaceflight/status/1733696945087230419

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LANDSPACE shares more renderings of 660t Zhuque-3. Stainless steel, methane and reusable.

https://twitter.com/cnspaceflight/status/1733705836994887990

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18*2 = 36 Starlink-style satellites per launch?
mp.weixin.qq.com/s/qNSp-DPOY_H_…

Brigantine · « **Reply #13 on:** 12/10/2023 09:51 pm »

If only they would announce the upper stage to use Starship-compatible on-orbit methalox refueling.

Upper stage propellant mass should be similar to what a single Starship tanker can supply to LEO, so with 2 re-usable launches and 1 LEO docking operation, something like
12 tonnes can be sent direct to Saturn,
7.5 tonnes to Neptune, or
18 tonnes to Jupiter (e.g. launching Europa Lander directly, instead of on SLS with gravity assists)

(assuming upper stage can fit 120 tonnes of propellant & 5 tonnes dry mass)

yuebai · « **Reply #14 on:** 12/11/2023 01:30 am »

Quote from: Brigantine on 12/10/2023 09:51 pm

If only they would announce the upper stage to use Starship-compatible on-orbit methalox refueling.

Upper stage propellant mass should be similar to what a single Starship tanker can supply to LEO, so with 2 re-usable launches and 1 LEO docking operation, something like
12 tonnes can be sent direct to Saturn,
7.5 tonnes to Neptune, or
18 tonnes to Jupiter (e.g. launching Europa Lander directly, instead of on SLS with gravity assists)

(assuming upper stage can fit 120 tonnes of propellant & 5 tonnes dry mass)

Without a plan for secondary recovery, it may not be necessary to develop a secondary refueling function for this rocket, and it may even be counterproductive. As for compatibility with Starship, it is even more unnecessary. I don't see the possibility of using both together.

FutureSpaceTourist · « **Reply #15 on:** 12/12/2023 07:06 am »

https://twitter.com/cnsawatcher/status/1734484270989668562

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🚀 Following its huge successes this year, LANDSPACE announces its reusable Zhuque-3 LOX/methane rocket! Dec 2023 will see a 100m first-stage recovery test, with assembly & flight validations in 2024! Aimed for maiden flight readiness in 2025. Full HD:

Prettz · « **Reply #16 on:** 12/12/2023 08:00 pm »

If it has a horizontal T/E, why the need for such an incredibly complex launch tower?

catdlr · « **Reply #17 on:** 12/12/2023 08:48 pm »

Quote from: Prettz on 12/12/2023 08:00 pm

If it has a horizontal T/E, why the need for such an incredibly complex launch tower?

Vertical PL requirements. SpaceX will be doing the same soon for the AF, but probably use the mobile launch integration building instead of the Chinese/Indian method of those rotating "Clam-shell" structures enclosing the LV. Note that the video doesn't indicate a horizontal integration building or ramp leading up to it. There is a crane at the top of the Tower (Apollo type) to lift the payload canister up to the top of the LV, then ClamShell structures are moved in to surround and staff and then complete integration and last minute Payload. The horizontal T/E is only used for getting the rocket vertical from the rocket transporter. It's different, but the end result is the same, but allows vertical integration of certain payloads requiring that, otherwise the horizontal T/E could bring the entire LV with payload from the integration facility down the road.

FutureSpaceTourist · « **Reply #18 on:** 12/18/2023 03:24 pm »

https://twitter.com/harry__stranger/status/1736726812439494678

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Satellite imagery taken on 2023-12-17 shows that Landspace's reusable hopper vehicle may be on the test stand at Launch Complex 96.

Galactic Penguin SST · « **Reply #19 on:** 01/19/2024 07:27 am »

According to various reports it appears the test vehicle's first hop was successfully completed today. Official confirmation is pending.

Edit: The vehicle is apparently named "Zhuque-3 VTVL-1", 3.35 m diameter and 18.3 m long. A single TQ-12 engine from the Zhuque-2 stage 1 powers it with 50-110% thrust variability from the original 80 tonnes thrust.

This first flight lasts around 60 seconds to a maximum height of ~350 m. "Landing precision" was given as 2.4 m, landing speed 0.75 m/s, & at a pitch angle of ~0.14° & roll angle of ~4.4°.

https://twitter.com/raz_liu/status/1748265875554394507

https://twitter.com/raz_liu/status/1748266576053494056