Quote from: SmallKing on 07/06/2017 05:09 amDuring Long March Commercial Launch Users Conference today, CGWIC introduced some new rocketsCZ-734 CBC configuration and low cost CZ-8A which will have its maiden flight on 2019Are those images to scale? Because the CZ-8A looks pretty much like a CZ-7 without boosters, and since the boosters provide roughly 2/3rds of the liftoff thrust, how could the CZ-8A even lift off?
During Long March Commercial Launch Users Conference today, CGWIC introduced some new rocketsCZ-734 CBC configuration and low cost CZ-8A which will have its maiden flight on 2019
As promised earlier, here are some of the new things found in this paper(*) written by people at CALT:(*) Qin X D, Long L H, Rong Y. The achievement and future of China space transportation system [J]Journal of Deep Space Exploration, 2016, 3 (4): 315-322- The often talked about CZ-8 is what some people once called the "CZ-722S" (and called CZ-822S here), using the existing CZ-7 first stage topped with the current hydrogen upper stage of the CZ-3 series as the 2nd stage. Two 120 t class, 2 meter diameter twin segment SRBs (thrust comparable with those on the Atlas V) are added to form the baseline version, capable of 4.5 tonnes to Sun-synchronous orbit (or 7.6 tonnes to LEO/2.5 tonnes to GTO). A "CZ-820" core only version can carries 3.0 tonnes to polar orbit.I personally don't think it to be cheap for heavier polar orbit missions (though it reminds me of the "Taurus II-mini-Centaur" that Antonio Elias mentioned 10 years ago on this forum, way before Antares flies, with similar performance), given the LH2 upper stage, but maybe CALT can find enough missions to make it work. It will face fierce competition with SAST's CZ-6A (not mentioned in this paper) though.- The GTO bound CZ-7 versions are called "CZ-3D" and "CZ-3E" in this paper (though I have seen different names in other papers). The CZ-7 + CZ-3 LH2 stage version is the "CZ-3D", 7.0 tonnes to GTO/4.2 tonnes to lunar transfer orbit and 3.0 tonnes to navigation sats MEO. A "CZ-3E" with the CZ-7 plus a RP-1 3rd stage with a single YF-115 engine is also mentioned that can lift 5.2 tonnes to GTO.(note however that the text paragraph calls the 1st stage as a "tri-core" configuration.....dunno if there's a mistake out there)As mentioned by me some time ago, the 3.5 stages combination doesn't look attractive to me in terms of costs and reliability, but maybe that's the best the Chinese can do right now.....- CZ-9's newest configuration ("CZ-934") seems to have 4 new 480 tonnes thrust twin chamber stage combustion RP-1 engines on a 10 meter diameter (some say 9.5) as the 1st stage, 4 boosters with 2 480 tonnes engines, 2 220 tonnes LH2 engines on 2nd stage (also 10 meters in diameter) and the existing CZ-5 upper LH2 stage as the 3rd stage. Performance were given as 140 t LEO/66 t GTO/50 t LTO/37 t MEO. Note however that the article also mentioned that the design is also comparable with large SRBs so the design is still far from frozen.....- CALT is studying an 4 stage solid air launch rocket dropped from the Y-20 military transport jet, with capability of no less than 200 kg to 700 km high polar orbits. - The name "YZ-3" has been confirmed for the SAST small sat upper stage that will fly on the CZ-2D and CZ-4 series, probably within this year.
- The GTO bound CZ-7 versions are called "CZ-3D" and "CZ-3E" in this paper (though I have seen different names in other papers). The CZ-7 + CZ-3 LH2 stage version is the "CZ-3D", 7.0 tonnes to GTO/4.2 tonnes to lunar transfer orbit and 3.0 tonnes to navigation sats MEO. A "CZ-3E" with the CZ-7 plus a RP-1 3rd stage with a single YF-115 engine is also mentioned that can lift 5.2 tonnes to GTO.(note however that the text paragraph calls the 1st stage as a "tri-core" configuration.....dunno if there's a mistake out there)
Quote- The GTO bound CZ-7 versions are called "CZ-3D" and "CZ-3E" in this paper (though I have seen different names in other papers). The CZ-7 + CZ-3 LH2 stage version is the "CZ-3D", 7.0 tonnes to GTO/4.2 tonnes to lunar transfer orbit and 3.0 tonnes to navigation sats MEO. A "CZ-3E" with the CZ-7 plus a RP-1 3rd stage with a single YF-115 engine is also mentioned that can lift 5.2 tonnes to GTO.(note however that the text paragraph calls the 1st stage as a "tri-core" configuration.....dunno if there's a mistake out there)This is actually somewhat of a surprise....which means that the Chinese are shifting away from the 2.25 m diameter rocket block. It might help somewhat with its cost, though given its capability is still 7 t GTO and that just half a day earlier some LSP did so with a 2-stage all kerolox rocket, it doesn't sound like a cheap solution at all.
That tri-core looks a bit FH inspired. (FH obviously won't be the first tri-core to fly, I know). But they really do seem to be following a weirdly scattershot strategy with launch vehicles. Why so much overlapping capability with so many configurations? Is it just for redundancy? Or just seeing what works best, and only the best will survive?Or is it launch site issues that force this? If they plan on flying most of these new LVs from Wenchang, I suppose it makes sense that all variants share a CZ-7 core stage.
Why produce the 2.25m core size when the 3.35m cores are common to the LZ-7 core and LZ-5 boosters. I realize the 2.25m tooling is common to the Long March 3 (LZ-3), but still seems silly.
Can they do high inclination launches from Wenchang?
Quote from: smfarmer11 on 07/08/2017 01:03 amCan they do high inclination launches from Wenchang?They have some options... Here is an image I made showing which directions they can launch out of.A) for GTO and low inclination (all CZ-5 and CZ-7 launches so far)B) SSO/polarC) depending on drop zones and Phillipine approval, they might be able to do higher inclination launches in this direction as well
As promised earlier, here are some of the new things found in this paper(*) written by people at CALT:- CZ-9's newest configuration ("CZ-934") seems to have 4 new 480 tonnes thrust twin chamber stage combustion RP-1 engines on a 10 meter diameter (some say 9.5) as the 1st stage, 4 boosters with 2 480 tonnes engines, 2 220 tonnes LH2 engines on 2nd stage (also 10 meters in diameter).....
http://mp.weixin.qq.com/s?__biz=MzA5MTQxODQ2MA==&mid=2649440048&idx=1&sn=3c6c23ca9d6e668d922aa9d89565619f&scene=23&srcid=0801SwBPU37Y12mlffVIA2e4#rd8月1日,由我院负责研制的重型运载火箭500吨级液氧煤油发动机首次燃气发生器-涡轮泵联动试验取得成功,标志着该型发动机研制工作取得首个里程碑式胜利,为后续圆满完成关深阶段研制任务奠定了基础。AAPLT: 500 tons LOX/Kero engine linkage test successfully for the first time
So basically the proposed CZ-9 design grows from 4 3+ meter boosters, 9 meter core, 2 stages (about a year ago) into 4 5+ meter boosters, 10+ meter core, 3 stages. For roughly the same performance? Interesting to see if this 6000+ ton monster grows any bigger.
ChinaSpaceflight just reported CZ-9 10m S1 and 5m strap-on would use YF480s, S2 would use staged-combustion YF220s and 25 ton expander cycle LH2/LOX engines for S3