Chinese orbital launcher projects

[TheKutKu]

I noticed there wasn't a general thread for this, so I created this since there are a lot of unrealised chinese launcher projects.

Starting with one that's already described on astronautix, but I'm posting a source, taken from Xiandong Bao "A Modular Space Transportation System" (IAF-92-0857) and also described in P.S. Clark (1999) JBIS, 52; Xiandong Bao was an engineer at what is now known as SAST, one of the main subsidiary of the Chinese astronautics giant CASC. This is one of the earlier proposals for a hydrocarbon-fuelled chinese launcher (although slightly earlier one were proposed during initial trade studies for the Shenzhou program)

The idea behind the paper is the development of a baseline two-stage launch vehicle. The Chinese paper notes that the first stage fuel would be a "hydrocarbon (CH)" and this is taken to refer to kerosene especially since the Chinese would later express an interest in purchasing Russian liquid oxygen/kero- sene engines (discussed later in this section).

The use of liquid oxygen and kerosene on the first stage of this vehicle would mark a departure for the Chinese, since they have previously used storable UDMH and a nitrogen-derived oxidizer (usually nitrogen tetroxide)

Data for the overall launch vehicle are:
Launch mass 377 tons
Payload capability 11 tons
Length 55 m
Diameter 4.5 m
Launch thrust 4.8 MN (490 tons-force)

On top of the second stage an instrument unit 1.6 metres high would be carried, acting as a data-collection and process- ing centre for the vehicle
The first stage would carry four engines which can gimble for control. The second stage a single main engine and a set of four verniers.

Taking this base design, it is proposed that a three-stage launch vehicle could be developed which could place 6 tonnes into geosynchronous transfer orbit: although not stated, one assumes that the third stage would use liquid oxygen and liquid hydrogen.

A series of different launch vehicles derived from the baseline launch vehicle's stages and the not-described third stage is proposed, leading to a maximum payload capability of 70 tonnes to the standard 60", 300-500 km reference orbit. For the larger payloads a fairing with a diameter of 5.4 metres and a length of 18 metres would be used.

The paper then speculates:

On the other hand, the Chinese have purchased an RD-120 engine. While the RD-120 itself has been used as the main engine on the second stage of the Zenit launch vehicle, the Russians are planning to introduce a modification designated RD-120K as the first stage of their new Rus/Soyuz-2 family of launch vehicles. It is not known whether the Chinese purchased the RD-120 itself or the more recent RD-120K modification.
One might speculate that if the launch vehicle family proposed in the 1992 IAF paper is being funded, then Chinese engines based upon what they have learned from studying the RD-120 technology could see an application of the first stage of the baseline launch vehicle. However, this is currently pure speculation.

Which of course turned out to be true. the YF-100 engine series was developped partially thanks to what was learned from studying a purchased ukrainian RD-120 (KRD-120 to be more accurate), more can be read here

 

[TheKutKu]

"A project of fully reusable verticaly launched launcher or "Chinese Kistler K-1"", 2000
Description from "Dragon Furieux: Les avions spatiaux chinois", Phillipe Coué, 2017

At the end of the 1990s, the "fever" of satellite constellations for mobile communications led private investors to believe that the market was sufficient to develop fully reusable and commercial launchers. Most of the initiatives were futuristic and had very little technical credibility. Other projects were only tax-saving operations accompanied by beautiful presentations and shiny websites.

However, in this American aerospace galore, the reusable two-stage K-1 launcher from Kistler Aerospace hit the headlines for several years and even reached the point of stage assembly and structural elements. It was perhaps its very classic (and therefore reassuring) configuration that had caught the attention of several potential customers such as NASA, which had at one time considered using the K-1 to resupply the International Space Station (ISS).


At the same time, the Beijing Institute of Astronautical Systems Engineering (part of Beihang University) took up the subject to reproduce the concept. The Chinese version of the K-1 was propelled by four Kerolox engines with 120 t of thrust (YF-100 class). This 35.2 m long launcher, with a maximum diameter of 5 m, would have sent 2 t in low orbit.

It could have been reused 50 times, while the engines would have to be replaced every 10 launches.

The article showcasing this project was published in the internal journal of CALT "Missiles and Space Vehicles", the article presented the recovery strategies and the simulations that had validated its feasibility.


When the "Chinese K-1" project was unveiled in 2000, Chen Lan, the owner of the "Go Taikonauts" website reported the rumor that this reusable launcher configuration was in competition with five other projects. The selection was expected at the end of 2000.

The mentioned news article can be read here: https://web.archive.org/web/2001042....com/CapeCanaveral/Launchpad/1921/news-23.htm
With the following low res picture of a drawing by Chen Lan (original isn't archived, I would appreciate if someone had the full version saved):

 

[Archibald]

And... here we go (grabs popcorn).

 

[cattalonX]

I saw this on weibo

 

[TheKutKu]

"A project of fully reusable verticaly launched launcher or "Chinese Kistler K-1"", 2000
Description from "Dragon Furieux: Les avions spatiaux chinois", Phillipe Coué, 2017

View attachment 744595

From Spaceships A Reference Guide to International Reusable -- Robert A Goehlich -- Burlington, Ontario, ©2006

 

[publiusr]

I am surprised no one cloned that--no barge, no hoverslam...

 

[RanulfC]

I am surprised no one cloned that--no barge, no hoverslam...

Still did a boost-back though

Randy

 

[cattalonX]

A lunar rocket concept from the early 21st century.I don't know what engine it's using, but it has a takeoff weight of 2,880 tons
However, considering the number of first stage engines is 7, then the engine thrust needs to be more than 420 tons, which is higher than the thrust of the YF135

 

[cattalonX]

An CBC variant of CZ3

 

[cattalonX]

 

[TheKutKu]

View attachment 759349View attachment 759350View attachment 759351View attachment 759352

The Aviation Week article and some additional context:



And what is being said on weibo

[New discoveries in space archaeology: Long March 2 four/eight boosters]
Around 1985, Huang Zuoyi, a launch vehicle expert, and Yu Menglun, a ballistics expert, jointly proposed the bundled rocket CZ2-4L. "CZ2" means that it is based on the Long March 2 series rocket with a diameter of 3.35 meters, and "4L" means adding four parallel liquid rocket boosters with a diameter of 1.65 meters (inseparable). The two form a bundled rocket with a low-orbit carrying capacity of 9,000 kilograms. With the appropriate upper stage, the synchronous transfer orbit carrying capacity is about 2,500 kilograms.
From the perspective of future development potential and overall rocket configuration, the plan also envisioned an alternative eight-booster configuration, further increasing the LEO payload from 9,000 kg to 13,500 kg.

This proposal was introduced to the international market to gauge interest and received positive feedback from potential Western launch service clients, including the United States. China Great Wall Industry Corporation (CGWIC) conducted 24 technical promotional presentations for major U.S. communications satellite manufacturers, satellite operators, space insurers, and aerospace consulting firms. The CZ2-4L rocket concept attracted significant attention, with clients generally agreeing that its design and technical capabilities met the needs of the next-generation communications satellites.

With the promising momentum in the launch services market, the design team initiated feasibility studies on the bundled rocket in 1987. The CZ2-4L was renamed LM-2E (Long March 2E). While largely retaining the original CZ2-4L concept, several modifications were made to the rocket’s overall configuration:

• The booster diameter was increased from 1.65 meters to 2.25 meters, as the 1.65-meter structure had been discontinued.
• The boosters were made separable, instead of being permanently attached.
• The fairing diameter was expanded from 4.0 meters to 4.2 meters.
• The LEO payload capacity was increased from 9,000 kg to 9,500 kg.

This proposal was previously featured in the documentary Shaking the Heavens (撼天记 ; available on bilibili, part 3 or 4 I think), though at the time, there was insufficient textual documentation to substantiate the details.