NASASpaceFlight.com Forum
International Space Flight (ESA, Russia, China and others) => Japanese Launchers => Topic started by: zaitcev on 05/05/2010 12:07 am
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http://www.senkyo.co.jp/ists2008/pdf/2008-a-04.pdf
Is there a project site somewhere? I see nothing at http://www.jaxa.jp/projects/index_j.html
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Interesting, to use an expander (bleed) on a first stage. This has been proposed before but has been left unexplored for some reason.
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Here is good background information.
Mitsubishi Pushes For H-IIA And H-IIB Replacement
http://www.aviationweek.com/Article.aspx?id=/article-xml/AW_10_15_2012_p28-504957.xml
About a quarter of Japan's space engineers—those who have had the most experience developing the H-II series and its predecessors—will retire by 2020, Asada said at the Japan International Aerospace Exhibition here last week. By 2020, an engineer who was 25 in the mid-1980s, during early work on the original H-II rocket, will be around 60.
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More on Japan's proposed H-X:
http://www.b14643.de/Spacerockets_1/Japan/H-X/Description/Text.htm
http://archive.ists.or.jp/upload_pdf/2011-a-21.pdf
http://archive.ists.or.jp/upload_pdf/2009-a-04.pdf
See also:
http://forum.nasaspaceflight.com/index.php?topic=20286.msg972102#msg972102
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H-X (H-3) development might be started next JFY.
In Japan, positive news are reported. It will be including next JFY budget request.
But budget problem is still exist. So, may be started small budget.
A first flight is targeted for 2021.
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About H3
3-2
http://www8.cao.go.jp/space/comittee/yusou-dai3/gijisidai.html
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Kicking off this update thread for H-3 as there is now an official advise from the Japanese government:
http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY (http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY)
Japanese Government Recommends Developing H-2A Successor
A high-level Japanese government panel has tentatively recommended proceeding with development of a lower-cost, commercially viable successor to the nation’s workhorse H-2A rocket.
The recommendation to develop the so-called H-3 rocket was handed down May 17 in a draft midterm report by the Space Transportation Systems Subcommittee of Japan’s Cabinet-level Office of National Space Policy (ONSP).
H-2A prime contractor Mitsubishi Heavy Industries (MHI) of Tokyo proposed a two-stage “New Concept Rocket” with a liquid-fueled core stage and solid-rocket strap-on motors that would be available commercially by 2020 at half the price of an H-2A
Note: the H-X thread and the H-3 development thread were merged into one as both handle the same subject: the proposed H-IIA successor.
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Kicking off this update thread for H-3 as there is now an official advise from the Japanese government:
http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY (http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY)
Japanese Government Recommends Developing H-2A Successor
A high-level Japanese government panel has tentatively recommended proceeding with development of a lower-cost, commercially viable successor to the nation’s workhorse H-2A rocket.
The recommendation to develop the so-called H-3 rocket was handed down May 17 in a draft midterm report by the Space Transportation Systems Subcommittee of Japan’s Cabinet-level Office of National Space Policy (ONSP).
H-2A prime contractor Mitsubishi Heavy Industries (MHI) of Tokyo proposed a two-stage “New Concept Rocket” with a liquid-fueled core stage and solid-rocket strap-on motors that would be available commercially by 2020 at half the price of an H-2A
Note: the H-X thread and the H-3 development thread were merged into one as both handle the same subject: the proposed H-IIA successor.
"at half the price of an H-2A" this is an impressive goal. Can't wait to see how this is done.
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Kicking off this update thread for H-3 as there is now an official advise from the Japanese government:
http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY (http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY)
Japanese Government Recommends Developing H-2A Successor
A high-level Japanese government panel has tentatively recommended proceeding with development of a lower-cost, commercially viable successor to the nation’s workhorse H-2A rocket.
The recommendation to develop the so-called H-3 rocket was handed down May 17 in a draft midterm report by the Space Transportation Systems Subcommittee of Japan’s Cabinet-level Office of National Space Policy (ONSP).
H-2A prime contractor Mitsubishi Heavy Industries (MHI) of Tokyo proposed a two-stage “New Concept Rocket” with a liquid-fueled core stage and solid-rocket strap-on motors that would be available commercially by 2020 at half the price of an H-2A
Note: the H-X thread and the H-3 development thread were merged into one as both handle the same subject: the proposed H-IIA successor.
"at half the price of an H-2A" this is an impressive goal. Can't wait to see how this is done.
Won't become a reality. CNES recently said something very similar about Ariane 6. Won't happen either. (the "half the price" bit I mean)
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Kicking off this update thread for H-3 as there is now an official advise from the Japanese government:
http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY (http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY)
Japanese Government Recommends Developing H-2A Successor
A high-level Japanese government panel has tentatively recommended proceeding with development of a lower-cost, commercially viable successor to the nation’s workhorse H-2A rocket.
The recommendation to develop the so-called H-3 rocket was handed down May 17 in a draft midterm report by the Space Transportation Systems Subcommittee of Japan’s Cabinet-level Office of National Space Policy (ONSP).
H-2A prime contractor Mitsubishi Heavy Industries (MHI) of Tokyo proposed a two-stage “New Concept Rocket” with a liquid-fueled core stage and solid-rocket strap-on motors that would be available commercially by 2020 at half the price of an H-2A
Note: the H-X thread and the H-3 development thread were merged into one as both handle the same subject: the proposed H-IIA successor.
"at half the price of an H-2A" this is an impressive goal. Can't wait to see how this is done.
Won't become a reality. CNES recently said something very similar about Ariane 6. Won't happen either. (the "half the price" bit I mean)
Any cost savings at this time are like a must, so I wish them well in the project. Also hope the USA still has some ties to JAXA and can get these cost savings ideas/designs transferred to Delta.
You missed something I hope wasn't a translation issue. It said "commercial" in that statement. As you know most of the current launches are for JAXA.
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Kicking off this update thread for H-3 as there is now an official advise from the Japanese government:
http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY (http://www.spacenews.com/article/launch-report/35499japanese-government-recommends-developing-h-2a-successor#.UaXk7di3kZY)
Japanese Government Recommends Developing H-2A Successor
A high-level Japanese government panel has tentatively recommended proceeding with development of a lower-cost, commercially viable successor to the nation’s workhorse H-2A rocket.
The recommendation to develop the so-called H-3 rocket was handed down May 17 in a draft midterm report by the Space Transportation Systems Subcommittee of Japan’s Cabinet-level Office of National Space Policy (ONSP).
H-2A prime contractor Mitsubishi Heavy Industries (MHI) of Tokyo proposed a two-stage “New Concept Rocket” with a liquid-fueled core stage and solid-rocket strap-on motors that would be available commercially by 2020 at half the price of an H-2A
Note: the H-X thread and the H-3 development thread were merged into one as both handle the same subject: the proposed H-IIA successor.
"at half the price of an H-2A" this is an impressive goal. Can't wait to see how this is done.
Won't become a reality. CNES recently said something very similar about Ariane 6. Won't happen either. (the "half the price" bit I mean)
Any cost savings at this time are like a must, so I wish them well in the project. Also hope the USA still has some ties to JAXA and can get these cost savings ideas/designs transferred to Delta.
You missed something I hope wasn't a translation issue. It said "commercial" in that statement. As you know most of the current launches are for JAXA.
No, I didn't miss that. Like ESA, the Japanese launchers are developed under auspices of the space agency. In this case JAXA. It then will be put to work as a commercial launcher. This is not Mitsubishi saying: "Hey, we're gonna develop H-3 on our own and market it commercially". This is Mitsubishi saying: "Hey JAXA, we have a proposal for an HII-A replacement and guess what... it has a chance of being fielded commercially. Would you kindly supply us with the funds needed to develop this thing?". With the latter they 'sold' a government advice council on the viability of their proposal and now that government council is giving the advice to actually fund and develop H-3. With Japanese taxpayers money naturally.
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More on Japan's proposed H-X:
http://www.b14643.de/Spacerockets_1/Japan/H-X/Description/Text.htm
http://archive.ists.or.jp/upload_pdf/2011-a-21.pdf
http://archive.ists.or.jp/upload_pdf/2009-a-04.pdf
Interesting.
It uses a new open exander cycle engine, LE-X, with a thrust of 1448kN (vac) and an ISP of 432.
The core stage has two LE-X. Then there is a second stage AND a small third stage for GTO launches (curious). Apparently the version without boosters can put 4t to GTO. For 6t to GTO the launcher requires 4 additional boosters.
I guess it depends on how cheap those LE-X will be...
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Latest study material.
H-3 family launch capability (upside) and H-2A/H-2B launch capability illustration.
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With the ongoing currency war and the massive yen deface to come, they might even become commercially attractive.
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Latest study material.
H-3 family launch capability (upside) and H-2A/H-2B launch capability illustration.
Interesting. Pretty much resembles the liquid A6 configuration, with LE-X instead of Vulcain 3 (almost same specs).
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LINK: http://e.nikkei.com/e/fr/tnks/Nni20130918D17HH036.htm
Wednesday, September 18, 2013
Mitsubishi Heavy Eyes Commercialization Of Rocket Tech
TOKYO -- Mitsubishi Heavy Industries Ltd. is also eyeing commercialization of low-cost rocket launches in line with the nation's official strategy.
It took a giant leap in its bid to become a profitable space company on Aug. 4 when it launched one of its H-IIB rockets for the first time after it took over full control of launch services from Japan's space agency, at the Tanegashima Space Center in Kagoshima Prefecture.
The No. 4 H-IIB rocket carried into space the Konotori cargo transporter, which brought food and supplies to the International Space Station.
Ceding authority
For the launch of the first three H-IIB rockets, the Japan Aerospace Exploration Agency (JAXA) gave the final go-ahead after analyzing weather and other conditions. This was the first launch in which JAXA handed over all decision-making authority to Mitsubishi Heavy.
The company had previously been given the reins to launch the less powerful H-IIA rocket, and the Aug. 4 H-IIB launch marked another step in the privatization of Japan's space program.
The H-IIA and H-IIB are capable of putting satellites weighing up to 6 and 8 metric tons, respectively, into geostationary orbit.
With JAXA ceding its authority to Mitsubishi Heavy, the leading Japanese heavy machinery maker will be able to seek orders for launching domestic and foreign-made satellites of various sizes.
"We hope to market our services in Asia, the Middle East and elsewhere," said Yoichi Kujirai, executive vice president and head of aerospace systems at Mitsubishi Heavy.
The depreciation of the yen, coupled with JAXA's decision, has created "business opportunities for us at last," a Mitsubishi Heavy marketing official said.
Uncompetitive
The H-IIA and H-IIB face tough competition from overseas. The U.S. and Russia have launched more than 300 rockets between them; Japan has launched just over 20.
Mitsubishi does not disclose earnings from its rocket launch business, only that it is "not in the red," according to an official, suggesting that the business is not highly profitable for the company.
"Business is tough, but we hope to accumulate successful results," Executive Vice President Tatsuhiko Nojima said.
The rocket is "overlooked on the commercial market because of its high launch cost," said a JAXA official.
The H-IIA has secured only one launch order from abroad. The cost of each launch is estimated at nearly 10 billion yen ($100 million) for the H-IIA and 15 billion yen for the H-IIB, much higher than the global average of around 7 billion yen. Although the two rockets have high success rates, they do not compete with rivals on price.
According to Mitsubishi Heavy, it needs to carry out four launches a year to support its H-II rocket production technology. But only three launches are planned for this business year.
The government recently decided to begin a project in fiscal 2014 to develop an internationally competitive rocket, tentatively called the H-III. The successor to the H-IIA is expected to cost less while continuing to be as reliable. The project will involve JAXA, Mitsubishi Heavy, IHI Corp. and others.
Going private, cheaper
The high cost of the H-IIA program is the result of a government policy that regarded space as a testing ground for advanced technologies. The H-III project will seek to halve the cost of launches to encourage more commercial endeavors.
In past projects, the government decided on basic designs and then farmed out the development of rockets to private companies. The H-III program will take into account opinions and input from Mitsubishi Heavy and other companies from its initial stage.
The H-III project, with its slogan of "a rocket incorporating private-sector power," will consider the capabilities of solid-fueled rockets, and study new approaches to fuel efficiency and other cost-saving techniques. Foreign companies may also be asked to participate in the development of the engines and some other core components.
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Image Captions:
Image 1
Mitsubishi Heavy on Aug. 4 launches an H-IIB rocket after taking full control from JAXA at the Tanegashima Space Center in Kagoshima Prefecture. (Kyodo)
Image 2
Yoichi Kujirai, executive vice president and head of aerospace systems at Mitsubishi Heavy, speaks to the press after the successful launch of an H-IIB rocket on Aug. 4.
Image 3
An H-III rocket rests on a launch pad in this conceptual image provided by JAXA.
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LINK to MHI Business Briefing on Aerospace Systems (Includes H-III Dev Project): http://www.mhi.co.jp/en/finance/library/business/pdf/aero2012.pdf
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JAXA requested bids for H-III work on Feb 27, 2014. This must be for R&D at this stage.
http://www.spaceflightnow.com/news/n1403/04h3rocket/#.UxnVjs5Af6c
The claim that H-III will be cheaper and therefore competitive is identical to the claims made for H-IIA and even H-II. The truth seems to be that JAXA is planning for a bigger rocket with more lifting capability that is in many ways a growth variant of H-IIA/H-IIB. The big difference is a core that can lift itself for smaller payload missions, and a single core that can handle both H-IIA and H-IIB class missions, plus a bit more, by varying the number of solid boosters. I suppose that maintaining production of only one core instead of two should save a bit of money, but I still don't see the commercial competitiveness.
- Ed Kyle
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...but I still don't see the commercial competitiveness.
It seems to be a rocket optimized for institutional missions. I don't know why JAXA should get into the comsat business, IMO the market cannot support that many players. It probably barely pays off for ESA with 50%+ market share.
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...but I still don't see the commercial competitiveness.
It seems to be a rocket optimized for institutional missions. I don't know why JAXA should get into the comsat business, IMO the market cannot support that many players. It probably barely pays off for ESA with 50%+ market share.
And they launch from 30deg. So they have to spend more energy than even the Americans. With Japanese labor I don't see them being very competitive. But they engine should be a lot cheaper. The LE-7 is an RS-25 class engine, and probably cost wise very similar, with an annual production around of 4. The new core would use two of the cheaper LE-X (8?9?).
But cost is not only on the core, but on the ops. If they redesign the ground ops, have a true single core, simplified fairing offerings, and apply some of the low cost approach on avionics and GSE of the Epsilon, then they might lower costs.
The only issue is that by going the strap-a-solid for payload flexibility, they are sticking to vertical assembly. Will they do like Atlas V, and use an MLP, or should they do like Delta IV should have done and have checkout and integration done in an HIF time on the pad just for strap-on and payload integration.
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The LE-7 is an RS-25 class engine, and probably cost wise very similar
Only in terms of the cycle, otherwise not quite. The specs of the LE-7A vs RS-25
Thrust: 1,098 vs 2,279kN
CC pressure: 12.0 vs 20.6MPa
ISP (sl/vac): 338/440 vs 366/452s
Its actually at the upper end of what you could do with a GG (pressure, isp), surprising they went with SC.
http://en.wikipedia.org/wiki/LE-7
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New information from JAXA about the H-III?
http://www.jaxa.jp/press/2014/03/20140325_rocket_e.html?utm_source=dlvr.it&utm_medium=twitter
[ Special features ]
- The main liquid-engine core rockets will be the same specifications for all launch vehicles in the new series so that manufacturing and operation can be more efficiently performed.
- Up to six solid rocket boosters (depending on the needs) can be attached for a Geostationary Transfer Orbit (GTO) mission to be able to flexibly cope with diversified needs.
[ Development schedule ]
The development will begin in early Japan Fiscal Year 2014 targeting a maiden launch in JFY 2020.
[ Development details ]
- Launch vehicle development (structure, electronics/avionics, propulsion system, payload fairing)
- Engine development (for the first and second stages)
- Solid rocket booster development
- Launch pad, launch site ground facility development
So a modified H-IIB, but with a core capable of being flying without solids?
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At the IAF spring meeting in Paris last week, it was named "H-X".
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At the IAF spring meeting in Paris last week, it was named "H-X".
Wow, Launch cost reduction by Half. Impressive program.
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I hope they take a hard look at all the Delta IV lessons because it was supposed to be the dirty cheap launcher and ended up as a black sheep that only survived because of very questionable tactics of its parent company. I hope they are successful.
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At the IAF spring meeting in Paris last week, it was named "H-X".
Wow, Launch cost reduction by Half. Impressive program.
In my opinion, that "reduction by half" claim is based on the fact that both H-2A and H-2B will be replaced by this new vehicle. Two production lines reduced to one. That doesn't make it a cheap rocket.
- Ed Kyle
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At the IAF spring meeting in Paris last week, it was named "H-X".
Wow, Launch cost reduction by Half. Impressive program.
In my opinion, that "reduction by half" claim is based on the fact that both H-2A and H-2B will be replaced by this new vehicle. Two production lines reduced to one. That doesn't make it a cheap rocket.
- Ed Kyle
You might be right Ed.....However I get the impression Mitsubishi wishes to be a serious player in the launch business. Noticed this last launcher (GPM) was cheaper to make. The program now in place seems designed to be a continuous cost reduction, could add up real fast.
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At the IAF spring meeting in Paris last week, it was named "H-X".
Wow, Launch cost reduction by Half. Impressive program.
In my opinion, that "reduction by half" claim is based on the fact that both H-2A and H-2B will be replaced by this new vehicle. Two production lines reduced to one. That doesn't make it a cheap rocket.
- Ed Kyle
Since the H-3 is not developing new engines or new tooling. The development cost should be minimal.
Of course the cost estimate and the actual cost might be quite different.
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At the IAF spring meeting in Paris last week, it was named "H-X".
Wow, Launch cost reduction by Half. Impressive program.
In my opinion, that "reduction by half" claim is based on the fact that both H-2A and H-2B will be replaced by this new vehicle. Two production lines reduced to one. That doesn't make it a cheap rocket.
- Ed Kyle
Since the H-3 is not developing new engines or new tooling. The development cost should be minimal.
Of course the cost estimate and the actual cost might be quite different.
Nope, new first and second stage engines and new SRBs....... ::)
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In many ways, H3 and A6 seem to tread the same path now, yet in very different countries / cultures.
Its a very difficult challenge to address a low cost LV involving solids/hydrolox. Delta IV went from the potential of cheap to the reality of extreme expense. Commonality to reduce cost fights optimality to achieve vehicle performance. Presumption of high launch frequency - a common political over reach, predestines failure to reach cost targets before vehicle obsolescence.
And then the cycle starts anew, as the components of the launch system including vehicle either are shared/not evolved enough and the past cost/performance/scale burdens are inherited from the past, or too much is novel for not enough gain in this cycle of development.
Atlas was a excellent study in caution from a technical/operations perspective. Incremental refinement that invested but did not over invest in the future. But perhaps this caution indirectly and unavoidably caused a vulnerability in the form of dependancy - if say one could have determined the future, would Atlas V with an American kerolox engine (perhaps from TRW?) from the Atlas II days ... been as much of a success? Or was the dependency/outsourcing also much of the success of Atlas V?
Likewise, Musk added significant risk in F9.1.1/F9R. Have though about kevinrf's "every LV over reaches market demand" while watching the roll out of it.
As well as the potentially successful overreach of ATK's Advanced Boosters for SLS as follow on post EM 1/2 flights, against the backdrop of an OrbATK merger and unclear follow-on for SLS given potential global economic instabilities being signalled.
The nature of industry integration (Japan/Europe) or of CONOPs operation (Musk's reusability) or of forcing strategic funding (ATK/Russia/others) as competing means to address the future launch services, the ways forward don't seem clear.
"What you can do" vs. "what you should do" is clouded by industrial biases/practices/social/culture issues.
Clearly the only way forward is to reuse/leverage/scale/volume the past propulsion w/o additional costs or unneeded new development. In this case, common solids with Epsilon (is this possible?), a common engine for US/1 stages (works against optimal stage design), low cost common stage/tank construction. None of this was possible for A5/DIV. And it goes against both European and Japanese practice/culture. Its even worse if one talks about pad flows/GSE/"issues".
Also clear is that should Musk get practical reusable launch services, he'll own them globally for 5-10 years just with what is already developed and launching at the moment. Meaning many countries LV's might likely never see much launch frequency, making follow-on development of future LV's much more uncertain/uneconomic.
Pride/reliance could become very costly. How do very smart people facing this choose how to play out the near future?
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If they use an expander open cycle for the upper stage engine, they could probably do a niner like the F9, just with H2. So at least in that sense the Japanese don't appear to be doing any sort of dead end development.
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Interesting, to use an expander (bleed) on a first stage. This has been proposed before but has been left unexplored for some reason.
As I understand it, it's tough to get high pressure with an expander cycle, and that's an issue for an engine that must operate at sea level. But if it's an open expander cycle (has that ever been used before?), then that eases the problem a bit.
EDIT: "ease" to "eases"
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The LE-X engine is an open expander-bleed cycle; dumping the hydrogen used in the expander wastes the chemical energy content (though it may be manifolded into the exhaust nozzle downstream of the throat), but generates more turbopump power since the expander sees more of a vacuum rather than trying to stuff mass into the high pressure combustion chamber in a fully closed cycle as the RL10 and Vinci engines do. It's really more of a greatly scaled-up LE-5A/B, as used on the second stage.
https://www.mhi-global.com/company/technology/review/pdf/e484/e484036.pdf
There are a lot of ways to build a rocket engine, with sub-sets of design paths, and I'm having fun trying to discover and follow those different designs.
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If you like that look for a full flow expander that Aerojet worked on.
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This article (http://asia.nikkei.com/print/article/71422) shows a CGI image by JAXA of the H-III being raised from a horizontal position on a strongback.
(http://i.imgur.com/elbFlzc.jpg)
-Are the solid rocket boosters small and light enough for this to work, or does it have to be all-liquid?
-Will the VAB be dismantled and replaced with a horizontal integration facility, or will the rocket still be assembled vertically, then lowered to a horizontal position for transport to the launch pad?
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This article (http://asia.nikkei.com/print/article/71422) shows a CGI image by JAXA of the H-III being raised from a horizontal position on a strongback.
(http://i.imgur.com/elbFlzc.jpg)
-Are the solid rocket boosters small and light enough for this to work, or does it have to be all-liquid?
-Will the VAB be dismantled and replaced with a horizontal integration facility, or will the rocket still be assembled vertically, then lowered to a horizontal position for transport to the launch pad?
appears to use the H-II family pads. Other info shows that H-III will be made launch site flexible like Epsilon so there may be additional pads elsewhere
Also the TEL design in some previous graphic show it is only employed on the core alone version but that was 2013.
EDIT: Existing MLs will be modified and reused for H-III (H-X)
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Latest report on the H-III - it has passed the mission definition and system readiness review phase.
Looks like the team is still looking at the core stages with the number of engines on both stages still undecided (2-3 for the 1st stage and 1-2 for the 2nd), and they seems to have went back to vertical integration.
Hmm....while I still hold on to some expectations, I'm sure that some fans of a certain SoCal aerospace company will say that this one will also be "obsolete by next Monday". ::)
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Latest report on the H-III - it has passed the mission definition and system readiness review phase.
Looks like the team is still looking at the core stages with the number of engines on both stages still undecided (2-3 for the 1st stage and 1-2 for the 2nd), and they seems to have went back to vertical integration.
SDR is finished and agreed transition to the preliminary design phase.
The team is decided 1st stage engines number are selectable 2 or 3.
2nd stage number of engines (1 or 2) are not defined yet.
Modified SRBs are selectable 0 or 2 or 4.
Launch pad ML2 is upgraded for this rocket.
This next generation rocket's name is not defined yet. H-III is not official name.
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So the solid boosters will mostly be the same as H-IIA/B instead of having two to six smaller SRBs?
If H-III and H-X aren't official names, what else would they call it? H-IIC?
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So the solid boosters will mostly be the same as H-IIA/B instead of having two to six smaller SRBs?
If H-III and H-X aren't official names, what else would they call it? H-IIC?
Yes, they will be a derivative of the SRB/A A3 version employed on Epsilon LV and H-IIB, BUT with different attachment and separation system.
As for naming I can't say except MHI calls it only H-III and JAXA calls it H-X in most documents.
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It seems that Japanese media is reporting a target cost of 50 billion yen (~$41M US) for the baseline version - if so that's a little bit higher than what I think for the (similar performance) basic F9R....but not by much. If they really can hit that target the Japanese might actually have some chance of getting a foothold in the market for the very first time. ;)
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Looks very Atlas V like. Does it has some defined target performances?
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This is an update thread. Lets move H-III discussions here: http://forum.nasaspaceflight.com/index.php?topic=37263.0
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Looks very Atlas V like. Does it has some defined target performances?
6-7 metric tons /GSO.
H-IIA is 4.6 ton, H-IIB is 5.5 ton.
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http://global.jaxa.jp/press/2015/07/20150702_h3.html
Announcement of the Official Naming of the Next Generation Launch Vehicle
The National Research and Development Agency, Japan Aerospace Exploration Agency (JAXA) is proud to announce the official naming of the Next Generation Launch Vehicle currently under development as follows. The name was decided in coordination with the prime contractor (Mitsubishi Heavy Industries, Ltd.)
We will continue to develop the Next Generation Launch Vehicle in order to achieve flexible and diversified demands.
Name: H3 Launch Vehicle (Abbreviation: H3)
The major reasons for the selection is as follows:
The “H” stands for a successful heritage of our H-IIA/H-IIB Launch Vehicles.
The “3” implies our innovative challenge.
http://www.jaxa.jp/press/2015/07/files/20150702_rocket_j.pdf
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http://global.jaxa.jp/press/2015/07/20150702_h3.html
Announcement of the Official Naming of the Next Generation Launch Vehicle
The National Research and Development Agency, Japan Aerospace Exploration Agency (JAXA) is proud to announce the official naming of the Next Generation Launch Vehicle currently under development as follows. The name was decided in coordination with the prime contractor (Mitsubishi Heavy Industries, Ltd.)
We will continue to develop the Next Generation Launch Vehicle in order to achieve flexible and diversified demands.
Name: H3 Launch Vehicle (Abbreviation: H3)
The major reasons for the selection is as follows:
The “H” stands for a successful heritage of our H-IIA/H-IIB Launch Vehicles.
The “3” implies our innovative challenge.
http://www.jaxa.jp/press/2015/07/files/20150702_rocket_j.pdf
In other news, it looks like they have settled on 1 140 kN thrust engine on the upper stage - which according to Japanese reports would be an upgrade of the existing LE-5B rather than a new engine.
The first stage will have either 2 or 3 new 1.5 MN class engines (LE-9) - I guess it will be 2 on the GTO bound versions with SRBs and 3 on the baseline SSO version? The SRBs will have an average thrust of 2.2 MN.
It seems that Japanese media is reporting a target cost of 50 billion yen (~$41M US) for the baseline version - if so that's a little bit higher than what I think for the (similar performance) basic F9R....but not by much. If they really can hit that target the Japanese might actually have some chance of getting a foothold in the market for the very first time. ;)
OK it's 5B yen not 50, but the target cost is holding. It won't be a game changer, but $40M US for a 4+t SSO launcher might be able to sink the Ariane 62, Vega-E and Antares 200..... ::)
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Well, I applaud them for this! It will be an exciting project of the nature that Vulcan is.
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http://global.jaxa.jp/press/2015/07/20150702_h3.html
Announcement of the Official Naming of the Next Generation Launch Vehicle
The National Research and Development Agency, Japan Aerospace Exploration Agency (JAXA) is proud to announce the official naming of the Next Generation Launch Vehicle currently under development as follows. The name was decided in coordination with the prime contractor (Mitsubishi Heavy Industries, Ltd.)
We will continue to develop the Next Generation Launch Vehicle in order to achieve flexible and diversified demands.
Name: H3 Launch Vehicle (Abbreviation: H3)
The major reasons for the selection is as follows:
The “H” stands for a successful heritage of our H-IIA/H-IIB Launch Vehicles.
The “3” implies our innovative challenge.
http://www.jaxa.jp/press/2015/07/files/20150702_rocket_j.pdf
In other news, it looks like they have settled on 1 140 kN thrust engine on the upper stage - which according to Japanese reports would be an upgrade of the existing LE-5B rather than a new engine.
The first stage will have either 2 or 3 new 1.5 MN class engines (LE-9) - I guess it will be 2 on the GTO bound versions with SRBs and 3 on the baseline SSO version? The SRBs will have an average thrust of 2.2 MN.
It seems that Japanese media is reporting a target cost of 50 billion yen (~$41M US) for the baseline version - if so that's a little bit higher than what I think for the (similar performance) basic F9R....but not by much. If they really can hit that target the Japanese might actually have some chance of getting a foothold in the market for the very first time. ;)
OK it's 5B yen not 50, but the target cost is holding. It won't be a game changer, but $40M US for a 4+t SSO launcher might be able to sink the Ariane 62, Vega-E and Antares 200..... ::)
Yes, it is an upgraded LE-5B, which has potential to get new designation LE-5C upon project completion because of enhancements and next gen design for additive manufacturing. The upgraded engine will be replaced with a new engine as part of a future upgrade package, which may become H-IIIA. This replacement is not planned till a minimum of a decade from now.
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Press Conference on H3 rocket
Scheduled for Jul 8, 2015
National Research and Development Japan Aerospace Exploration Agency (JAXA), 2014 to the development of H3 rocket towards to it embarked on a (2014) year, 2020 year of testing machine launch Unit 1, to implement the current basic design doing. About H3 rocket under development, its aim appearance and system do the description of the beam outline. -
Days when: July 8, 2015 (Wed)
15:30 - 16:30 , the presenter and explained the contents (. titles omitted, presentations is working title)
in 1991 about rocket JAXA first space technology sector H3 project team project manager Tadashi Okada (Okada Masashi) sub-manager Makoto Arita (Arita Makoto) Business Promotion Department Planning Manager Yuji Mori (Mori Yuji)
16:00 - 16:30 Q & A
https://youtu.be/d9Z4TtQIZ4g
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Press Conference on H3 rocket
Streamed live on Jul 8, 2015
National Research and Development Japan Aerospace Exploration Agency (JAXA), 2014 to the development of H3 rocket towards to it embarked on a (2014) year, 2020 year of testing machine launch Unit 1, to implement the current basic design doing. About H3 rocket under development, its aim appearance and system do the description of the beam outline. -
Days when: July 8, 2015 (Wed)
15:30 - 16:30 , the presenter and explained the contents (. titles omitted, presentations is working title)
15:30 ~ 4:00 PM in 1991 about rocket JAXA first space technology sector H3 project team project manager Tadashi Okada (Okada Masashi) sub-manager Makoto Arita (Arita Makoto) Business Promotion Department Planning Manager Yuji Mori (Mori Yuji)
16:00 - 16:30 Q & A
https://youtu.be/d9Z4TtQIZ4g
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H3 Press Conference document
http://fanfun.jaxa.jp/jaxatv/files/jaxatv_20150708_h3.pdf
That was good press conference.
LE-9 thrust is more than 10 times bigger than LE-5B, how develop the such large scale leap ? (LE-9 thrust is 150 metric tons, LE-5B 14 tons)
The point is longer thrust chamber that collect more heat from chamber wall (LE-5B, LE-9 are Expander breed cycle engine).
SRB-A is almost newly developed. Visual appearance is same, but another one.
Here is Japanese text script.
http://ima.hatenablog.jp/entry/2015/07/08/153000
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Any word regarding reusability?.
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looks like they are targeting around 14 flights a year initially from only pad 2. Launch rate would double if pad 1 converted.
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Any word regarding reusability?.
im not great at Japanese, but it appears answer is no.
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Any hard data one the LE-9? I would like to write a wikipedia article.
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Any hard data one the LE-9? I would like to write a wikipedia article.
Ill compile what i find into a PM for you.
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looks like they are targeting around 14 flights a year initially from only pad 2. Launch rate would double if pad 1 converted.
They planed only 1 pad operations for cost saving.
And Pad 2 can handle both H3 and H-IIB launch.
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Any word regarding reusability?.
im not great at Japanese, but it appears answer is no.
Sorry to late reply.
Answer is no. H3 project is not planed reusability
But, another JAXA project studied reusable rocket technology for future H3. Still concept study level.
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Impressive looking hardware and concepts! I wish I could read Japanese. Anyone catch the performance to Low Earth Orbit for the 4x SRB version - both 28.5 degree or other low-inclinations and 50+plus degree orbits?
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The LE-9 would be by far the highest thrust expander cycle engine ever developed, using a "bleed" or open cycle rather than a closed cycle turbopump system. Getting that much thrust out of an expander cycle turbopump is a challenge: the specific impulse is lower as a result of the open cycle, but it's still pretty good. I wonder what the T/W ratio is?
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Would they human rate the H3. I was thinking of SNC DC in regards to this.
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Would they human rate the H3. I was thinking of SNC DC in regards to this.
initally no. That would be mandatory to do so under separate joint MHI/JAXA project. Since there ia not a crew project it is yet to be planned in the development schedule
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Whatever happened to the HTV-derived vehicle (http://forum.nasaspaceflight.com/index.php?topic=19061.0)?
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Whatever happened to the HTV-derived vehicle (http://forum.nasaspaceflight.com/index.php?topic=19061.0)?
Never got past the concept phase.
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Peter B. de Selding @pbdes 6 minutes ago
Japan's Jaxa: H-3 rocket to launch from 2020, 6,500kg to GTO, being designed w/ MHI esp for commercial market.#IAC2015
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Talking Space @talkingspace 28 minutes ago
Tsutomu Fukatsu, @JAXA_en, is introducing a new launch vehicle, H3, in 2020 to compete for commercial $ #IAC2015
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Here is another article on this topic:
http://www.spaceflightinsider.com/organizations/jaxa/japan-shows-off-its-space-ambitions-with-upcoming-htv-flight/
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Official information: H3 version IDs are released :)
H3-abc: a=Number of LE-7 (2 or 3), b=Number of SRB-3 (0 or 2 or 4), c= Fairing size (S or L)
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Here's a text file dump of a Google translation of the pdf file on the previous message.
- Ed Kyle
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They want to have a common motor for SRB-3 and Epsilon first stage. Only difference would be the nosecap and the H3 solids would not use TVC (but will try to use as many common parts of the nozzle as possible).
PDR early 2016, CDR late 2017, first launch 2020. They should be starting to build the engine test stand about now.
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6,500 kg or more to GTO. $45 million per launch for base version.
http://www.parabolicarc.com/2016/05/19/jaxa-outlines-plans-h3-launch-vehicle/#more-58435
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This article (http://asia.nikkei.com/print/article/71422) shows a CGI image by JAXA of the H-III being raised from a horizontal position on a strongback.
(http://i.imgur.com/elbFlzc.jpg)
-Are the solid rocket boosters small and light enough for this to work, or does it have to be all-liquid?
-Will the VAB be dismantled and replaced with a horizontal integration facility, or will the rocket still be assembled vertically, then lowered to a horizontal position for transport to the launch pad?
I know this doesn't matter anymore in regards to the current plan, but it turns out that there would have been enough room for a horizontal vehicle assembly building between the current VAB and the block house (I came across the image here (http://danielmarin.naukas.com/2014/03/14/h-3-el-nuevo-cohete-japones/))
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Current status of the H3 Preliminary Design. (Japanese document)
http://www.jaxa.jp/press/2016/06/files/20160614_h3_01_j.pdf
H3 PDR is finished.
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The logo mark of H3 Development
http://jda.jaxa.jp/result.php?lang=e&id=e7aeb542fe44aa91cf0842ef6bfef8f3
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Jaxa Today No.10.
They talk about H3 development from page 6 to 9.
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Second Stage LE-5B LRE Upgrade now identified as LE-5B-3
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Launch pad ML2 is upgraded for this rocket.
I learn something new, there were three ‘movable launchers’.
https://www.mhi-global.com/products/expand/rocket_launcher_supply_result_03.html
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Launch pad ML2 is upgraded for this rocket.
I learn something new, there are three ‘movable launchers’.
https://www.mhi-global.com/products/expand/rocket_launcher_supply_result_03.html
yes and if launch rate ever becomes high enough all three can be upgraded to H-3 configuration
ML-2 is the only one still moved on rails and ML3 is the one that also hosts H-IIB (It basically lives in that configuration currently).
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From the JAXA presentation on UNOOSA meeting in Vienna:
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Jaxa have posted a new video of the H-3
https://youtu.be/aKtAxNVv0Wc
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LE-9 test engine #1 photos.
http://jda.jaxa.jp/result.php?lang=j&id=06dff376756d0df623d702256a0be7a2
http://jda.jaxa.jp/result.php?lang=j&id=6150686e52bc6e456a0242d59f624357
JAXA's LE-9 homepage
http://www.rocket.jaxa.jp/engine/le9/
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MHI says H3 rocket development on track for 2020
by Caleb Henry — June 26, 2017
http://spacenews.com/mhi-says-h3-rocket-development-on-track-for-2020/ (http://spacenews.com/mhi-says-h3-rocket-development-on-track-for-2020/)
Article includes:
Ko Ogasawara, MHI’s vice president and general manager for launch, told SpaceNews the critical design review, or CDR, for the H3 is scheduled for this autumn and will give an indication of how effective the company has been at reducing costs.
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LE-9 test engine #1 photos.
http://jda.jaxa.jp/result.php?lang=j&id=06dff376756d0df623d702256a0be7a2
So does this use tube-wall or channel-wall regen nozzle cooling?
The pumps, etc, look a lot more elegant and simpler than most first stage engines. An advantage of the expander cycle I guess. I wonder how many restarts this engine can do in theory? Or how deep it can throttle.
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Close view shows channel-wall nozzle (with reinforced ribs?)
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Close view shows channel-wall nozzle (with reinforced ribs?)
Just out of curiosity, what are some visual things that give away that a nozzle/bell is channel-wall? (Sorry if this would drift off-topic)
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Close view shows channel-wall nozzle (with reinforced ribs?)
Just out of curiosity, what are some visual things that give away that a nozzle/bell is channel-wall? (Sorry if this would drift off-topic)
Some engines (like the F-1, SSME, and M1C) have cooling pipes that are painstakingly welded/attached to the inside and/or outside of the nozzle well. (see http://heroicrelics.org/info/f-1/f-1-thrust-chamber.html )
Channel wall nozzles have these pipes engraved/printed right into the nozzle wall itself, which is easier to automate and creates a flatter, simpler, and more efficient structure. Virtually all newer regeneratively cooled engines use this method.
So since the outside of the nozzle appears to have a flat surface, the assumption is that it uses channel wall cooling.
Please correct me if I am wrong. :)
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So since the outside of the nozzle appears to have a flat surface, the assumption is that it uses channel wall cooling.
Well that really wasn't the response I was expecting. I obviously meant visual cues besides "it's not a tube-wall".
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I was lazy. Assuming there are no tubes, so it must be channel walled.
Found "Visualization and Optimization of LE-X Engine System Margin", the nozzle extension (or nozzle skirt) is cooled by turbine outlet gas. Seems the gas is just dumped into the nozzle extension. There is no regenerative cooling channel.
Another feature is elongated combustion chamber. For some reason, the combustion chamber is called upper chamber. The nozzle is called lower chamber.
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That LE9 is just a beautiful engine - stunning piece of hardware!!
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According to "Combustion Stability Improvement of LE-9 Engine for Booster Stage of H3 Launch Vehicle" from Mitsubishi Heavy Industries Technical Review Vol. 53 No. 4 (December 2016)
...hydrogen with its pressure decreased when driving the turbo pump enters into the nozzle, and flows along the adjacent of the wall surface while cooling it (film cooling).
There is a diagram noting "Flowing along nozzle internal wall (film cooling)".
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There is a discussion thread so use it people: H3 Development Discussion Thread (http://forum.nasaspaceflight.com/index.php?topic=37263.0).
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Translate yourself:
使いやすいロケットを目指して~LE-9ターボポンプ単体試験~
JAXA | 宇宙航空研究開発機構
JAXA角田宇宙センターでは、LE-9エンジンに使われるターボポンプの単体試験が行われています。
ターボポンプはエンジンに燃料(液体水素)と酸化剤(液体酸素)を供給する重要な構成品です。
この試験ではターボポンプに実際に燃料と酸化剤を流して設計通りの機能・性能を発揮できたか確認しています。
ターボポンプはLE-9エンジンに取り付けられてエンジン燃焼試験が開始されました。
▽ ロケットナビゲーター(第一宇宙技術部門)
http://www.rocket.jaxa.jp/
https://www.youtube.com/watch?v=w0oj1h9uuoM
次世代大型ロケット「H3」新型エンジン「LE-9」燃焼試験(実機型#1-1)
JAXA | 宇宙航空研究開発機構
JAXAが開発を進める次世代大型ロケット、「H3」の第1段エンジン「LE-9」の燃焼試験が種子島宇宙センターで始まっています。「LE-9」にはJAXAが10年以上にわたり研究に取り組んできたエキスパンダブリードサイクルを採用。これまでのエンジンを上回るパワーと安全性の両立を目指しています。
▽ ロケットナビゲータ | LE-9
http://www.rocket.jaxa.jp/engine/le9/
https://www.youtube.com/watch?v=3n6xq-9DSrk
EDIT: videos were replaced with amended versions so links have been replaced.
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Here is the translation.
"Aiming at easy-to-use rocket-LE-9 Turbo pump Unit Test
JAXA | Aerospace Research and Development Organization
The JAXA Tsunoda Space Center has a unit test for the turbo pump used in the LE-9 engine.
The turbo pump is an important component of supplying fuel (liquid hydrogen) and oxidizing agent (liquid oxygen) to the engine.
In this test, we have confirmed whether the turbo pump was able to demonstrate the function and performance as designed by actually shedding fuel and oxidizing agent.
The turbo pump was installed in the LE-9 engine and the engine combustion test was started.
Rocket Navigator (Cosmic Air Technology Division)
http://www.rocket.jaxa.jp/"
"Next-generation large rocket "H3" new Engine "LE-9" combustion test (actual type # 1-1)
JAXA | Aerospace Research and Development Organization
The combustion test of the first-stage engine "LE-9" of the next-generation large-scale rocket, "H3", which JAXA develops begins at Tanegashima Space Center. "LE-9" employs an expander bleed cycle that JAXA has been working on for more than ten years. We aim to balance the power and safety exceeding the previous engine.
Rocket Navigator | le-9"
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JAXA New LE-9 Rocket Engine
https://www.youtube.com/watch?v=phUbQkdznw0
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MHI technial review no: 54/4 is out and its talks about H-3
http://www.mhi.com/company/technology/review/Vol.54No.4/indexe-54-4.html
edit/gongora: attached the H3 update as well as a couple other space related papers from that link
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I don't know if there's anything new here (maybe launch rate?), but this article (https://asia.nikkei.com/Business/Companies/Building-on-success-of-flagship-rocket-Japan-to-take-on-low-cost-rivals2) in the Asian Nikkei Review comments on the H3;
Mitsubishi Heavy and JAXA aim to launch a prototype of the H3, the H-IIA's successor, in fiscal 2020. The goal is to slash costs to around 5 billion yen ($45.3 million) and the time from order to launch to about one year, using shared parts and components sourced from the private sector. The rocket will also be able to be fitted with different numbers of solid rocket boosters to adjust thrust capacity.
"In both price and reliability, the H3 will put up as good a fight or better" than competitors like SpaceX, said Naohiko Abe, Mitsubishi Heavy's senior vice president in charge of space systems, adding that he hoped to launch two to three satellites per year.
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【Re-edited version】 H3 rocket LE 9 real machine engine combustion test live relay
JAXA | Japan Aerospace Exploration Agency
Published on Jul 3, 2018
The LE-9 (Lee Nine) engine is a rocket engine that is being newly developed as a main engine of a new rocket "H3 (H3)" scheduled for the launch of the first machine in 2020. As part of this development, burning tests are continuing on April 2017 at the Tanegashima Space Center's combustion test facility. The purpose of this burning test is to obtain various data by repeating the tests with different operating conditions such as thrust and to check whether the function, performance, durability etc are as designed. This burning test is performed for about 240 seconds, using the second experimental engine. We have carried out seven tests so far and accumulated combustion results of about 1,150 seconds. The burning test at this stage is a challenge for each test to be unknown. During combustion, we monitor the operating condition of the engine, and if we get data beyond predicted, we will stop the engine safely. And we use the obtained data in the next exam. The live pattern of the burning test will be live from the Tanegashima Space Center large rocket launch site located about 550 m from the test facility. Please experience the development of the large liquid rocket engine through the image.
● Relay Date Heisei era June 25 (Monday)
● Scheduled air time 15: 45 ~ (planned)
● Please be aware of ※ This distribution will be carried out experimentally with the cooperation of Nikon Corporation is. * Depending on the progress of the examination and weather conditions, the distribution date/delivery time etc. may change or be canceled abruptly. Please note. ※ The burning time is a standard. The burning time may be shortened depending on the acquisition of technical data. ※ This test result will be posted on HP at a later date.
https://youtu.be/99fplB9McyY?t=001
https://youtu.be/99fplB9McyY
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SRB - 3 Ground burning test Tanegashima Lighthouse fixed point camera / Solid Rocket Booster - 3 Motor Burning Test
NVS
Started streaming 12 minutes ago (from date timestamp of this post)
We will deliver the state of the SRB - 3 ground burning test for the H - 3 rocket from the Tanegashima lighthouse by the unmanned fixed point camera. Expected to be tested (DATE): 2018/8/25 11:00 around and around 11:00 + 0900 (JST) ※ Tanegashima The lighthouse is normally restricted from entry. Please do not enter unauthorized entry. ※ For unattended delivery using mobile line, delivery may be canceled without notice.
https://youtu.be/N5XotdgRPMk?t=001
https://youtu.be/N5XotdgRPMk
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Solid rocket booster for H3 rocket (SRB - 3) ground relay combustion test live relay
JAXA | Japan Aerospace Exploration Agency
Started streaming 2 hours ago
Solid rocket booster SRB-3 (SR B-3) of a new rocket "H3 (H3)" planned to be launched in FY 2020 for the first test machine. This time live broadcast from the Tanegashima Space Center Takezaki Observatory on site, located about 900 m from the ground burning test site, of the SRB-3 test flame test called "actual machine type motor". Please feel the development scene of the H3 rocket through the image. <Combustion Test Details> SRB-3 for test called "actual machine type motor" was ignited by placing solid fuel in the motor case which is a fuel tank, and it was confirmed whether the characteristics at the time of combustion were as intended I will. The data obtained from this test will be reflected in the design of SRB-3 for flight. The solid rocket booster is responsible for supplementing the thrust immediately after launch, and after burning for about 100 seconds, it finishes its task and is separated from the rocket. In the H3 rocket, you can replace this SRB - 3 with 0, 2, 4, so you can launch artificial satellites of various sizes. Combustion test date and time: August 25, Saturday, August 30, broadcast scheduled time: around 10:50 to 11:0510:50~11:05頃10:50~11:05頃10:50~11:05頃
https://youtu.be/tsKeIXHS0uM?t=001
https://youtu.be/tsKeIXHS0uM
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Report of scrub due to wind direction per NVS chat. Standing by to here if they will switch to the second window of the day at 1300JST. The NVS live stream will run until the camera battery shuts the camera down.
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Report of scrub due to wind direction per NVS chat. Standing by to here if they will switch to the second window of the day at 1300JST. The NVS live stream will run until the camera battery shuts the camera down.
Per NVS: Today's test ended in a scrub due to weather (winds and wind direction (for high speed engineering camera recording)). Currently working a NET 24 hour recycle pending favorable weather. The second test window is currently a no go.
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JAXA MHI/IHI consortium had a nominal static fire test today. Teams are processing data from the test. No translations at this time:
SRB-3地上燃焼試験@竹崎観望台
NVS
Streamed live 12 hours ago
燃焼試験は 24:00 より
H-3ロケット用SRB-3地上燃焼試験の様子を竹崎観望台より配信します。
NVSのメンバーは対応できない為、鳥嶋真也さん(@kosmograd_info)に対応頂けることになりました。
燃焼試験予定時刻 2018/8/26 16:00
なお、実験に適した風向きにならない場合は、実験時間の変更や
再度延期する場合もございます。
https://www.youtube.com/watch?v=U6InruG-ciw
and
H3ロケット用固体ロケットブースタ(SRB-3) 地上燃焼試験ライブ中継
JAXA | 宇宙航空研究開発機構
Streamed live 12 hours ago
2020年度に試験機1号機の打ち上げが予定されている新型ロケット「H3(エイチスリー)」の固体ロケットブースタSRB-3(エスアールビー・スリー)。
この度、「実機型モータ」と呼ばれる試験用のSRB-3の燃焼試験の模様を、地上燃焼試験場から約900mの位置にある、現地、種子島宇宙センター竹崎展望台からライブ中継します。
H3ロケットの開発現場を映像を通じて体感ください。
<燃焼試験詳細>
「実機型モータ」と呼ばれる試験用のSRB-3を、燃料タンクであるモータケースに固体燃料を入れて点火し、燃焼時の特性などが設計意図どおりであるかを確認します。この試験により得られたデータをフライト用SRB-3の設計に反映します。
固体ロケットブースタは、ロケット発射直後の推力を補う役割を担っており、約100秒燃焼した後、役目を終え、ロケットから切り離されます。H3ロケットではこのSRB-3を0本、2本、4本と付け替えることができるため、様々な大きさの人工衛星を打ち上げることができます。
燃焼試験日時:平成30年8月26日(日)
放送時刻:15:50~16:05頃
https://www.youtube.com/watch?v=gTUiSAlpkYs
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SRB-3 static fire test
SciNews
Published on Aug 30, 2018
JAXA conducted a ground firing test of SRB-3, the Solid Fuel Rocket Booster for the H3 launch vehicle, at the Ground Combustion Test Facilities for Solid Rocket of the Takesaki launch site at the JAXA Tanegashima Space Center, on 26 August 2018, at 07:00 UTC (16:00 local time). According to JAXA, the test lasted 110.1 seconds and was considered successful, with a maximum thrust of 2137 kN.
Credit: JAXA
https://youtu.be/qQt0NbWVAhY?t=001
https://youtu.be/qQt0NbWVAhY
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Very interesting, thank you! :)
Can you tell what the source is and whether it's allowed to share the images?
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I notice LE-9 is 33% heavier than LE-7 for 33% more thrust, despite using a vastly simpler engine cycle. Shouldn't the weight gain be less than that, all other things being equal?
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I notice LE-9 is 33% heavier than LE-7 for 33% more thrust, despite using a vastly simpler engine cycle. Shouldn't the weight gain be less than that, all other things being equal?
Some slides from next week's presentation at the IAC in Bremen. They are in the public domain.
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H3-32 configuration was deleted. H3-32 was consolidated to the H3-22 configuration.
http://www.jaxa.jp/press/2018/11/files/20181129_h3.pdf
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https://www.mhi.com/news/story/181206.html
Inmarsat to be first commercial customer for the new H3 launch vehicle provided by MHI
-The H3 will start commercial launch services in 2022-
2018-12-06
London/Tokyo, December 6, 2018 - Inmarsat (LON: ISAT), the world leader in global mobile satellite communications, has today announced that it has entered into an agreement with Mitsubishi Heavy Industries, Ltd. (MHI) to be the first commercial customer to place an order for the new H3 launch vehicle. The maiden flight of H3 is scheduled for 2020 with Inmarsat planning to deploy the new launch vehicle after 2022.
This is the second agreement entered by Inmarsat and MHI, following the launch services contract awarded to MHI's H-IIA Launch Vehicle in 2017. These agreements underline the growing partnership between the two companies in the area of launch services.
Rupert Pearce, CEO of Inmarsat, said: "Inmarsat is the world leader in global mobile satellite communications; a position we have achieved by building an exceptional ecosystem of partners. As our company grows - expanding into new markets and opening up new opportunities for our customers to develop their businesses - we continually seek new technology partners that display an outstanding commitment to innovation and excellence.
"It was for these reasons that in 2017 we selected MHI as a launch partner and why today we are delighted to be announcing that Inmarsat is the first commercial customer to select MHI's new H3 launch vehicle. We believe that H3 represents a world-class innovation and one that will deliver an effective and efficient service to place future Inmarsat satellites into orbit."
"Today, development of the H3 Launch Vehicle is proceeding steadily forward under the leadership of the Japan Aerospace Exploration Agency (JAXA), with MHI serving as primary contractor working closely with key component manufacturers," said Masahiro Atsumi, Vice President & Senior General Manager for Space Systems at MHI. "We greatly appreciate the high evaluation made by Inmarsat during this development phase and, working closely with JAXA and government agencies, we will do everything possible to ensure that development results in a new flagship launch vehicle fully meeting the customer's high expectations."
Rt Hon Greg Clark MP, Secretary of State for Business said: "Science and innovation have no borders, as long-term strategic partnerships like this one built on excellence between Inmarsat in the UK and MHI in Japan demonstrate.
"The space sector is a UK success story and an industry that is growing globally, a year since the launch of our modern industrial strategy, we continue to build on our commitment to space, including through the announcement of the UK's first spaceports and record investment in our world leading science base."
MHI Launch Services enjoys an extremely high success rate of 97.9% and has provided 41 successful consecutive launches since 2005, delivered on-time and to the customer's satisfaction by current launch vehicle both H-IIA and H-IIB.
The agreement with Inmarsat reflects MHI's long-term commitment to supporting a wide range of customers in the space industry. MHI will continue to support the development of the space industry, and will seek further new opportunities in this field both in Japan and globally.
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H3-32 configuration was deleted. H3-32 was consolidated to the H3-22 configuration.
Interesting. Based on a translation of the PDF (attached), the performance of the H3-22 config was greater than anticipated, making it more of a middle step between the light H3-30 and heavy H3-24 configs.
While H3-22 won't match the performance of cancelled H3-32, they'll simply change the reference orbits they offer for given payloads.
To justify this, they note that while GEO-1500m/s may be the "world standard" GTO, most of Falcon 9's launches have been with rather more than 1500m/s delta-V required on the satellite's part to get to GEO. As such, it would seem that sat operators would rather save money by launching on a smaller rocket and simply adding a few hundred more m/s of delta-V to their sat, then demanding a rocket capable of insertion into a strict GEO-1500 GTO.
This seems to be a valid conclusion to draw, and makes me wonder if JAXA isn't more attuned with the current and near future launch market than ESA. An H3 with half the performance but half the cost of an Ariane 6 would loft single satellites for the same cost as a launch on an Ariane 6, but without needing to wait for a partner comsat to be ready, as necessary with Ariane 5 and 6's standard dual launches. That's a nice competitive advantage...
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from the pdf:
https://forum.nasaspaceflight.com/index.php?action=dlattach;topic=21491.0;attach=1530988;sess=55234
MHI Standard launch price, which is calculated by the gluteal 【note 1 ] : about 50 Billion yen ( H3-30S )
about 50 Billion yen can not be right, probably 5 Billion yen
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from the pdf:
https://forum.nasaspaceflight.com/index.php?action=dlattach;topic=21491.0;attach=1530988;sess=55234
MHI Standard launch price, which is calculated by the gluteal 【note 1 ] : about 50 Billion yen ( H3-30S )
about 50 Billion yen can not be right, probably 5 Billion yen
Somehow 5 Billion Yen don't seems right either. Since that is about 44.5M USD.
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from the pdf:
https://forum.nasaspaceflight.com/index.php?action=dlattach;topic=21491.0;attach=1530988;sess=55234
MHI Standard launch price, which is calculated by the gluteal 【note 1 ] : about 50 Billion yen ( H3-30S )
about 50 Billion yen can not be right, probably 5 Billion yen
Somehow 5 Billion Yen don't seems right either. Since that is about 44.5M USD.
Rounded to the nearest billion Yen, that is about right for the smallest version. I've seen $50M mentioned before.
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If theres now only one 3-engine configuration (and its the smallest variant), I gotta wonder how much they're really saving with that vs simply ditching the zero-booster variant and using 2 SRBs on all flights. Liquid engines are usually pretty expensive compared to solids, not unreasonable to expect its close to the cost of an SRB pair. Plus the extra development and tooling cost of the unique parts for that version (I assume the engine section is largely unique), which will no longer be shared with H3-32L. Might allow more performance too, if it was re-optimized for that (pretty sure H3-22L's liftoff TWR is higher than H3-30S, so it might be possible to enlarge the tanks a bit)
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If theres now only one 3-engine configuration (and its the smallest variant), I gotta wonder how much they're really saving with that vs simply ditching the zero-booster variant and using 2 SRBs on all flights. Liquid engines are usually pretty expensive compared to solids, not unreasonable to expect its close to the cost of an SRB pair.
I used to think the 2- or 3-engine options with H3 were weird and counterproductive, but then I worked though the (very rough) financial numbers and H3-30 is probably worthwhile even without an H3-32 variant.
First, from what I can tell, SRB3s have around the same thrust as the upcoming Vulcan GEM-63XLs, but burn for around 10 seconds longer, making them somewhat more beefy. They're also half the thrust/size of Ariane 6's P120 solid motors.
Without a price step between the H3-22 and H3-24, it's hard to get a good read on SRB3 pricing, but putting them in the same price category as GEM-63XLs at maybe $8-10M each might be realistic. And $15-20M for a pair is a sizable chunk of money compared to the ~$50M price for an H3-30.
Second, the H3's expander-bleed LE-9 engine seems designed to be absurdly simple. As it doesn't even have to worry about igniting a gas generator and spinning up a turbine -- LE-9s just flow LH2, ramp the pumps and ignite the main chamber -- one might argue that it's even simpler than a Merlin 1D. That simplicity should substantially reduce costs compared to H2A's LE-7A staged combustion hydrolox engines, and if LE-9's ISP suffers a bit for it, well everyone knows ISP doesn't matter so much on a booster engine.
Now, if Vulcan's BE-4s are rumoured to be ~$16M/pair, then that's $8M an engine. Given that the BE-4 is an engine almost twice the size of an LE-9 and running a rather more complex ORSC cycle, the cost of an LE-9 should be rather less. It's possible that $5M is a reasonable figure.
As such, I'd guess that a pair of SRB3s are substantially more expensive than an additional LE-9, but obviously can't confirm it until we know the pricing of H3-30 versus H3-22.
Plus the extra development and tooling cost of the unique parts for that version (I assume the engine section is largely unique), which will no longer be shared with H3-32L.
JAXA/Mitsubishi are attempting to commercially compete with SpaceX using an expendable rocket, while also serving domestic institutional launch needs. As such, the H3-30 is like the Ariane 62 and probably not really meant for commercial use -- it's only a 4t+ SSO launcher, after all. Dropping the H3-30 variant would likely just penalize the costs of institutional launches -- forcing them to go on a pricier H3-22 -- while likely not saving much if anything on commercial GTO launches with either an H3-22 or -24.
Yes, the H3-30 will just need to bear the additional design and manufacturing costs associated with the second booster thrust section design, but with saving, say, $10M overall per flight (as above, adding maybe $5M for an LE-9 while avoiding maybe $15M for a pair of SRB3s), that probably won't take too many institutional launches.
Might allow more performance too, if it was re-optimized for that (pretty sure H3-22L's liftoff TWR is higher than H3-30S, so it might be possible to enlarge the tanks a bit)
The H3s don't really need bigger tanks for more performance -- they can lift anything required as it stands, with the H3-22 covering the electric and small chemical GEO sat market, and H3-24 covering heavy chemical GEO sats.
They really only need more performance if they're going to be recovered which, sadly, they're not.
Like Ariane 6, the H3 project had unfortunate timing -- Falcon 9 had been proven and had low pricing compared to anything else, but F9-R was very much in doubt when the projects started. Both, then, are aimed to compete with current F9 pricing per-sat and nothing more, and only ESA/JAXA's *next* architectures will compete with reusable rockets.
That said, I think a large clustered LE-9 design has... possibilities. ;-)
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If theres now only one 3-engine configuration (and its the smallest variant), I gotta wonder how much they're really saving with that vs simply ditching the zero-booster variant and using 2 SRBs on all flights. Liquid engines are usually pretty expensive compared to solids, not unreasonable to expect its close to the cost of an SRB pair. Plus the extra development and tooling cost of the unique parts for that version (I assume the engine section is largely unique), which will no longer be shared with H3-32L. Might allow more performance too, if it was re-optimized for that (pretty sure H3-22L's liftoff TWR is higher than H3-30S, so it might be possible to enlarge the tanks a bit)
Wonder if a H3-34L configuration with possibly upgraded/enlarged upper stage have any takers.
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If theres now only one 3-engine configuration (and its the smallest variant), I gotta wonder how much they're really saving with that vs simply ditching the zero-booster variant and using 2 SRBs on all flights. Liquid engines are usually pretty expensive compared to solids, not unreasonable to expect its close to the cost of an SRB pair. Plus the extra development and tooling cost of the unique parts for that version (I assume the engine section is largely unique), which will no longer be shared with H3-32L. Might allow more performance too, if it was re-optimized for that (pretty sure H3-22L's liftoff TWR is higher than H3-30S, so it might be possible to enlarge the tanks a bit)
Wonder if a H3-34L configuration with possibly upgraded/enlarged upper stage have any takers.
MB-60 engine was originally on the table with an ACES class/type US but to cut cost and accelerate H-3 development an enlarged and optimized H-2B US was brought over to H-3 with updated engine version called LE-5B-3 (RL10C-2 equivalent).
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ML about complete:
https://twitter.com/Cosmic_Penguin/status/1107974822590439424
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H-3 BFT LE-9 cluster test. Battleship test 1 of Core Booster:
https://www.youtube.com/watch?v=zM7UEtyKNX4
https://youtu.be/v2KrzkqdtvU
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A question to increase my bank of random trivia answers; has there been any other traditional rocket with a 3 engine cluster? There's the Shuttle, but I can't think of any booster with or even upper stage with 3 engines.
Atlas rose on three-engine thrust, though in stage-and-a-half configuration with two high thrust booster engines straddling a lower thrust sustainer engine.
- Ed Kyle
This is a reminder that this is an updates only thread. Please move all discussion to this thread's discussion thread.
https://forum.nasaspaceflight.com/index.php?topic=37263.0
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Newly assembled H-3 MLP (#4) moved from construction site to begin pad interface tests.
https://youtu.be/2YT89u_6910
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A lot of seaside video, but the action takes place between rollout at 38:30 til 45:30 and back again at 1:13:15 til 1:21:10. Then a shorter trip from 2:07:00 till 2:12:00 and back from 2:12:30 til 2:17:34.
At 2.18:30 the mobile platform is seen up close and it starts moving after a lot of honking at 2:18:30. It moves rather fast for such a big structure!
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H3 rocket mobile launcher run test (2019.6.24)
NVS
Published on Jun 30, 2019
[YouTube translated]
The H3 rocket is under development for the launch of the first aircraft in fiscal 2020. We also proceeded with the assembly of the mobile launcher to install the H3 rocket, and it was released for coverage on June 24, 2019. It was a test with a weight of 360 tons of rocket weight. After this, the test will proceed and the launch pad will be equipped for the installation of rocket equipment such as fuel piping.
https://youtu.be/uGRTp31PYag
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Next SRB-3 MOTOR test: https://youtu.be/9JqA4BKUz2M
More links to come later.
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New Movable Launcher for H3
https://www.youtube.com/watch?v=j7wrff2zH5Q
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NVS stream has started.
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Looks like area has been cleared of personnel.
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Somebody in a lift-fork driving around.
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People now walking around.
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Area is now clear.
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Now there are two people at top of the grey wall.
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Area now clear. The test window is from 10:00 - 18:00 local time (01:00 to 09:00 UTC), which opens in about 2 hours and 15 minutes.
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Door is open.
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Housing is rolling back. I believe we can see the nozzle.
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Housing has stopped moving.
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Fire hose test at left. Five minutes to window opening.
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Fire truck leaving the area.
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We're four minutes into the window.
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Sprinklers are on.
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Sprinklers are off and there is a siren!
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Ignition!
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T+1 minute.
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Burnout!
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Sprinklers are back on.
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Looks like the fire is out, but there is still a lot of smoke.
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Nozzle looks intact.
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Personnel are out doing some inspecting. Some smoke or steam still exiting the nozzle.
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A lot of personnel near the motor.
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A question to increase my bank of random trivia answers; has there been any other traditional rocket with a 3 engine cluster? There's the Shuttle, but I can't think of any booster with or even upper stage with 3 engines.
Atlas (Original balloon tank) Family, if you count the outboard engines.
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A question to increase my bank of random trivia answers; has there been any other traditional rocket with a 3 engine cluster? There's the Shuttle, but I can't think of any booster with or even upper stage with 3 engines.
Atlas (Original balloon tank) Family, if you count the outboard engines.
Ed Kyle could probably answer that. He is kind of a forum historian given what he posts. This is a discussion thread.
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H3 Fairing Separation Test
https://www.youtube.com/watch?v=7nxiXD0UFRU
The H3 Launch Vehicle is Japan’s new mainstay rocket with high flexibility, high reliability, and high cost performance. Through comprehensive analyses of user needs, we are now building an "easy-to-use rocket." On December 17, 2019, a fairing separation test was conducted at the Harima Works of Kawasaki Heavy Industries in Hyogo Prefecture. The fairing, attached to the top of a rocket, protects a satellite inside from the extreme pressure and heat during flight through the atmosphere. This test successfully demonstrated that the new fairing for H3 was split apart as planned by activating the separation mechanism in the same manner as in actual flights. Together with Japanese companies, JAXA will continue to make an all-out effort to develop the H3 Launch Vehicle with the aim of launching its first flight in JFY 2020.
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2020.02.13 H3ロケット用第1段厚肉タンクステージの燃焼試験 LE-9 3基クラスタ燃焼試験 速報版
Combustion test of the first thick tank stage for H3 rocket LE-9 3-unit cluster combustion test
https://youtu.be/tOWhm8jbO5M (https://youtu.be/tOWhm8jbO5M)
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Ground burning test of SRB-3
https://www.youtube.com/watch?v=MMx-mGbLKN0
Ground burning test of solid rocket booster (SRB-3)certified motor for H3 rocket
(Including gimbaling test for epsilon rocket 1st stage)
2020/2/29 (sat)
3 minutes between 11:00 - 19:00 (+0900 JST)
TNSC(TaNegashima Space Center)
https://www.youtube.com/watch?v=RJitR86EKBs
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2020.02.13 H3ロケット用第1段厚肉タンクステージの燃焼試験 LE-9 3基クラスタ燃焼試験 速報版
Combustion test of the first thick tank stage for H3 rocket LE-9 3-unit cluster combustion test
Text is unfortunately japanese: https://www.sacj.org/openbbs/
picture with 3 LE-9 engines :)
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https://twitter.com/RachelTortorici/status/1276311574114861057
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How the test looked.
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The first H3 rocket :)
Google translate from https://www.jaxa.jp/projects/rockets/h3/index_j.html
Updated July 27, 2020
Functional test of the first H3 rocket tester
At the Tobishima Plant of Mitsubishi Heavy Industries, Ltd., located in Aichi Prefecture, the 1-stage and 2-stage aircraft for the H3 rocket tester No. 1 are showing their appearance and conducting functional tests.
(Left photo) Lying majesticly is the first stage H3 rocket tester. The size is 5.2m in diameter and about 37m in length, which is equivalent to two cars on the Yamanote line. The cylindrical cream-colored parts that extend horizontally are the liquid hydrogen tank and liquid oxygen tank that carry fuel. Two 1-stage engines LE-9 are mounted on the lower part in front.
(Right photo) This is a two-stage fuselage of the H3 rocket tester No. 1. The cream-colored part is the liquid hydrogen tank, which had a diameter of 4 m for the H-IIA rocket, but 5.2 m for the H3 rocket. The LE-5B-3 engine (no nozzle installed) is combined with a liquid oxygen tank wrapped with silver-colored insulation. The two-stage fuselage is equipped with structural members that support the fuel tank, piping that guides fuel to the engine, and electrical equipment that controls the fuselage.
For the first time, I was able to get a sense of accomplishment at the same time as seeing how the components that had been hard to complete until now were assembled as an actual launch vehicle, and at the same time, I was more enthusiastic about the successful launch.
The functional test currently underway is the work of carefully checking the functions of many rockets one by one. Tests to check if the function of distributing power to each device is correct, tests to check if the signals from various sensors are output correctly, check for leaks in the pipes through which fuel passes, and check whether valves are operating correctly After conducting the test, perform the test to electrically connect the 1st stage aircraft and the 2nd stage aircraft and run the same sequence as at the time of launch, move each device and valve, and check whether the signal is output properly. I will.
This is the first functional test of the H3 rocket. When I started the functional test, there were parts that did not go as I expected, and I am working forward by solving them one by one. The appearance of the aircraft is imposing, but the contents are like a freshly born deer, and its feet are indistinct. In the first power distribution test, we put in switches of hundreds of items one by one and check the voltage output of that line. Various troubles occur, such as signals not being able to communicate properly due to a slight time difference. I would like to be able to send it out as a full-scale rocket before the factory is shipped.
There are some past rocket launch failures that we could have found during the functional tests at this factory. I would like to proceed with the confirmation work carefully so as not to overlook it. After successfully completing the functional tests at the factory, it is finally time to carry the first test aircraft to the Tanegashima Space Center, assemble the aircraft, and perform a comprehensive system test to check the interface with the ground equipment. The mountain top is finally visible as the test machine is launched. We will continue to challenge ourselves.
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https://global.jaxa.jp/press/2020/09/20200911-2_e.html
Change of Schedule for the H3 Launch Vehicle Project
September 11, 2020 (JST)
National Research & Development Agency
Japan Aerospace Exploration Agency (JAXA)
The Japan Aerospace Exploration Agency (JAXA) has been pressing forward with the development of the H3 Launch Vehicle. In the process, a technical problem was identified regarding the LE-9 first-stage engine, which is a new engine now under development. In order to address the problem in an appropriate manner, JAXA has decided to postpone the launch of the first test flight from the Japanese fiscal year (JFY) 2020 to JFY 2021 and that of the second test flight from JFY 2021 to JFY 2022.
JAXA will deal with the LE-9 engine-related problem in an appropriate manner and make an all-out effort for the successful launch of the H3 as a new Japan’s mainstay rocket.
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JAXA H3 and LE-9 briefings (in Japanese):
H3:
https://youtu.be/G6c8YR__k6g
LE-9:
https://youtu.be/_fz5MB1X0TE
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https://twitter.com/nvslive/status/1352888803619430400
H3ロケット試験機1号機が三菱重工業の飛島工場で報道公開されました。 #nvslive
Web translation:
H3 Rocket Testing Vehicle No.1 was unveiled to the press at the Mitsubishi Heavy Industries' Tobishima Plant.
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Side by side comparison of HII and HIII cores:
https://twitter.com/MHI_GroupJP/status/1352903907958267904
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Google translation:
Mitsubishi Heavy Industries unveils new rocket H3
The first new H3 rocket was unveiled at Mitsubishi Heavy Industries' Tobishima Plant (Aichi Prefecture) on the 23rd. It will be possible to launch a satellite that is one size larger and heavier than H2A. Launch costs will be reduced to about 5 billion yen, which is half that of H2A, by making most electronic components general-purpose products. It is scheduled to be launched next year and will be shipped to Tanegashima in Kagoshima Prefecture, where the launch site is located, at the end of January.
https://youtu.be/im3z7AsFSAA
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They should have kept the futuristic font for "NIPPON"/"JAPAN".
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https://twitter.com/MHI_GroupJP/status/1353251192579747845
The core of the first H3 rocket tester was shipped today in a special container.
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H3 rocket latest CG.
https://s3-ap-northeast-1.amazonaws.com/jaxa-jda/http_root/photo/P100013200/410017a4ce9e79ec8a599c4c4eea7046.png
https://s3-ap-northeast-1.amazonaws.com/jaxa-jda/http_root/photo/P100013202/8c6f5305bb74869963ede1ba4123f427.png
https://s3-ap-northeast-1.amazonaws.com/jaxa-jda/http_root/photo/P100013203/ddfd7a796a6ab032334bc616735d12db.png
Left to right H3-30S, H3-22S, H3-22L and H3-24L configuration.
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Newly arrived video.
H3 Test Flight#1 flight sequence CG
https://www.youtube.com/watch?v=athE2loTY1o&feature=emb_title
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https://twitter.com/mageshiman1025/status/1355568905788432387
Seems like the booster wanted to leave early?
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https://twitter.com/NVSreporter/status/1355582728134041603
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Newly arrived video.
H3 Test Flight#1 flight sequence CG
https://www.youtube.com/watch?v=athE2loTY1o&feature=emb_title
Why does it look like the H3 is sunken into the launch pad?
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Seems the tilt was (fortunately) not particularly harmful to the core stage: vehicle is on stand!
https://twitter.com/MHI_GroupJP/status/1356739175148515331 (https://twitter.com/MHI_GroupJP/status/1356739175148515331)
https://twitter.com/MHI_GroupJP/status/1356881358812024832 (https://twitter.com/MHI_GroupJP/status/1356881358812024832)
https://twitter.com/JAXA_jp/status/1356866311381426176
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Two solid rocket boosters have been attached to the core stage.
https://twitter.com/MHI_GroupJP/status/1358724757076647936
https://twitter.com/jaxa_wdc/status/1358870734697869319
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H3 Rocket Cryogenic propellant filling test(roll-out)
https://www.youtube.com/watch?v=PJqkrNFDlRs
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https://twitter.com/TylerG1998/status/1372016225862217728
The first H3 rocket built by JAXA/MHI has been rolled out to LA-Y2 at the Tanegashima Space Center for integrated tests/WDRs in preparation for its maiden launch.
We could see that flight take place in the coming weeks.
https://twitter.com/koumeiShibata/status/1371974779616432131
You can see that the H3 rocket is installed in the mobile launch pad. (2021/03/17 From the movement of the aircraft for cryogenic inspection)
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Just using this excellent article from back in September as an excuse to bump the thread. H3 is supposed to launch this year, but I've found nothing narrowing the launch date down further than that.
https://www.nasaspaceflight.com/2021/09/japan-h3-engine-certification-first-flight/
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https://twitter.com/cosmic_penguin/status/1483298907908022273?s=21
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Joint Press Briefing:
https://youtu.be/T8XvZ_pgtG4
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Joint Press Briefing:
https://youtu.be/T8XvZ_pgtG4
I watched this live. I don't speak Japanese and so got very little out of it, but there were a couple animation which were helpful. It seems that the LE-9 engine problem, which is going to keep H3 grounded for at least this quarter, involves the turbopump blade resonating. In the presentation, there was an animation where it looked like it was warping.
Here's the official documentation, which I'll probably run through google translate in a bit.
https://www.jaxa.jp/press/2022/01/20220121-1_j.html
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Joint Press Briefing:
https://youtu.be/T8XvZ_pgtG4
I watched this live. I don't speak Japanese and so got very little out of it, but there were a couple animation which were helpful. It seems that the LE-9 engine problem, which is going to keep H3 grounded for at least this quarter, involves the turbopump blade resonating. In the presentation, there was an animation where it looked like it was warping.
Here's the official documentation, which I'll probably run through google translate in a bit.
https://www.jaxa.jp/press/2022/01/20220121-1_j.html
From the presentation PDF (with the aid of google translate):
p.3/4 - Temperature increases during steady-state operation causes inner chamber walls to soften, then pressure transients from startup/shutdown causing inner chamber wall to deform and rupture. Chamber wall thickness to be increased. Startup & shutdown sequences to be modified (changes unspecified).
p.5/6/7/8 - Fuel turbopump blade fatigue from previously known vibration mode. Instrumented testing identified mode, and also identified flutter of blades when coupled with fluid flow. Multiple design changes to FTP blades and to pump housing geometry, also being proactively applied to OTP.
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H3 September 1st 1330 to 1500 JST Update:
https://youtu.be/WTvWaBeGNJM
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H3 September 1st 1330 to 1500 JST Update:
https://youtu.be/WTvWaBeGNJM
Relying on machine translation, but they do appear to still be aiming for a first launch in 2022.
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H3 September 1st 1330 to 1500 JST Update:
https://youtu.be/WTvWaBeGNJM
Relying on machine translation, but they do appear to still be aiming for a first launch in 2022.
Fiscal Year 2022, which ends next March.
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https://youtu.be/WwBkcyPQwko
2022年度の打上げを目指し、H3ロケット試験機1号機再始動。
H3 has got back on track toward its first flight in FY2022
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https://twitter.com/jeff_foust/status/1569707584994611202
Iwao Igarashi, MHI: found good solution to turbine vibration problems in engine for H3, proved it was effective. First H3 launch now projected this fiscal year (ends March 31); will announce date after static-fire tests in November. [Sep 13]
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[H3 Rocket Today's Photo] "Installing the LE-9 engine on the 1st stage aircraft" has been released. Please take a look.
https://twitter.com/JAXA_jp/status/1574307976248119296
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At the same time, the H3 rocket, which is being assembled at the Large Rocket Assembly Building VAB for the 1st Stage Full-scale Tank Stage Combustion Test (CFT), was also unveiled. Since the aircraft is under development, the shooting range was limited to the first step and the first step, but I would like to thank JAXA and MHI for the opportunity to shoot.
https://twitter.com/nvslive/status/1576912746121428993
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https://twitter.com/jaxa_jp/status/1582586241966493698
[H3 rocket today's photo]
"Satellite Fairing Coupling Operation (VOS)" has been released.
Please take a look.
https://fanfun.jaxa.jp/countdown/h3/index.html
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https://twitter.com/jaxa_jp/status/1582927107998420992
[H3 Rocket Topics]
"On approaching the final stage of development" has been released!
Project Manager Okada will tell you about the scene and preparations for the final stage of development.
Please take a look.
fanfun.jaxa.jp/countdown/h3/i…
#H3 #ロケット
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https://twitter.com/jaxa_jp/status/1587768192427995136
[press release]
Implementation of H3 Rocket Test Vehicle No. 1 1st Stage Actual Tank Stage Combustion Test
https://www.jaxa.jp/press/2022/11/20221102-2_j.html
Implementation of H3 Rocket Test Vehicle No. 1 1st Stage Actual Tank Stage Combustion Test
November 2, 2022
Japan Aerospace Exploration Agency
The Japan Aerospace Exploration Agency (JAXA) will conduct the first-stage actual tank stage combustion test as follows as part of the development test for the launch of the H3 rocket test vehicle No. 1 in 2022. ,i will let you know.
Record
Test purpose : Comprehensive confirmation of 1st stage propulsion system using actual tank
Contents of the test : Combining the actual tank and the LE-9 engine, the LE-9 engine is combusted in the same procedure as during launch, and the overall function is confirmed.
Implementation period : Sunday, November 6, 2022 to Monday, November 7, 2022
Location : Tanegashima Space Center Large rocket launch site
Please note that the test implementation period may change depending on the weather and work progress.
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NVS Captive Firing Test (AKA Flight Readiness Firing Test (this stage already conducted green run testing)) Event Livestreams:
H3 Captive Firing Test Overview Briefing Session:
https://youtu.be/Nga1FRED0F0
H3 Captive Firing Test:
https://youtu.be/ZSv7jMu6p6U
H3 Captive Firing Test Result Briefing:
https://youtu.be/o4kxYqI791E
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H3 rollout completed for the core's static firing test:
https://twitter.com/Cosmic_Penguin/status/1589191784521158656 (https://twitter.com/Cosmic_Penguin/status/1589191784521158656)
https://twitter.com/Cosmic_Penguin/status/1589197682081689600
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Nice shots of journey to pad
twitter.com/nvsreporter/status/1589212384354512896
The aircraft [rocket] movement started at 18:30 as scheduled, and it took about 30 minutes to arrive at LP2.
https://twitter.com/nvsreporter/status/1589212966444236800
H3 test machine No. 1 CFT specification that appeared from VAB.
twitter.com/nvsreporter/status/1589213428505538560
ML5 lower dolly fairing air conditioning truck.
https://twitter.com/nvsreporter/status/1589214074927484928
H3 test machine arriving at LP2.
"Daichi 3" and the logo of the Defense Acquisition Agency on the brand new short fairing.
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From the site of the medium-sized launch site, I am grateful that the mission logo can be seen almost directly in front of me.
https://twitter.com/mageshiman1025/status/1589323390875488258
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FRF/CFT completed firing portion now flight simulation running. Standing by test conductor success determination.
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https://twitter.com/tane_rocket/status/1589522166944763904
H3 rocket test machine No. 1 CFT
From 16:30 on November 6th
#CFT
#H3ロケット試験機1号機
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twitter.com/nvsreporter/status/1589521566949609479
https://twitter.com/nvsreporter/status/1589522650665484288
After all, the power of LE-9 x 2 units is amazing.
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Looks like the static fire was as long as expected (23 s), going by several long-distance recordings. Nothing obviously off-nominal in those views, pending official word.
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https://youtu.be/cKfj7ZlViu4
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CFT/FRF results briefing is underway on NVS via:
https://www.youtube.com/watch?v=o4kxYqI791E
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Nominal 25s firing.
Rocket back in its hangar.
https://twitter.com/telstar_freemgz/status/1589787755097493504
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Auto translations not great on these tweets:
twitter.com/mageshiman1025/status/1590295580630450177
Left: Cryogenic inspection (F0)
March 18, 2021 Right 1st stage actual tank stage combustion test (CFT T0)
On November 8, 2022, the day after each test, after the restrictions were lifted, the photographing time and weather conditions were different from the medium-sized launch site. is possible.
https://twitter.com/mageshiman1025/status/1590310526898573312
Similarly, the difference between the F0 aircraft and the T0 aircraft from the Takezaki launch site.
The fairing is long and short, and the position of the air conditioning duct hose on the umbilical tower side is different.
On the fairing side, the upper part of the long type is common with the short one, so it is in the same position.
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LE-9 test updates:
https://www.rocket.jaxa.jp/rocket/engine/le9/firingTest.html
Google translation
https://www-rocket-jaxa-jp.translate.goog/rocket/engine/le9/firingTest.html?_x_tr_sl=auto&_x_tr_tl=en
Implementation of LE-9 certified engine combustion test for H3 rocket
...
Test name LE-9 certified engine combustion test
Test purpose LE-9 Certified Engine Life Verification
period Sunday, October 23, 2022 to November 2022 (planned)
place Japan Aerospace Exploration Agency Tanegashima Space Center (Kagoshima Prefecture)
Number of tests 4 times (planned)
https://www-rocket-jaxa-jp.translate.goog/rocket/engine/le9/2022/221021.html?_x_tr_sl=auto&_x_tr_tl=en
1 Oct. 23, 240.8 sec. 11.24 MPa
https://www.youtube.com/watch?v=uAD6nLBxsjQ
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2 Oct. 29, 241.5 sec. 6.36 MPa
https://www.youtube.com/watch?v=d8VvaSP3r-8
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3 Nov. 4, 257.7 sec. 10.25 MPa
https://www.youtube.com/watch?v=n8yWKlNp_WA
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4 Nov. 10, 250.0 sec. 10.45 MPa
https://www.youtube.com/watch?v=fIJ4jeUJG5I
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Here's a video from yesterday. Seems to be a general update.
https://www.youtube.com/watch?v=YpMdBT_f2pw
EDIT: Here is the linked PDF: https://www.jaxa.jp/projects/files/youtube/cft-h3/h3_20221220_1.pdf
It seems like they had a couple of components that exceeded their allotted margins for vibrations, and an oxygen seal that was leaking after the test. Both are pretty simply fixes, so while probably quite annoying, that's actually pretty promising.
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And now this video. First launch on February 12th!
https://www.youtube.com/watch?v=2TllYYI1kNg
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Here's a video from yesterday. Seems to be a general update.
https://www.youtube.com/watch?v=YpMdBT_f2pw
EDIT: Here is the linked PDF: https://www.jaxa.jp/projects/files/youtube/cft-h3/h3_20221220_1.pdf
It seems like they had a couple of components that exceeded their allotted margins for vibrations, and an oxygen seal that was leaking after the test. Both are pretty simply fixes, so while probably quite annoying, that's actually pretty promising.
They have also replaced the pyrovalves used for pressurization of the 2nd stage RCS tanks due to possible relation with the failure of Epslion flight F6 this October (same manufacturer, same working principle, though different model), despite investigations still ongoing for Epsilon. A different vendor’s model used on the current H-IIA was substituted in.
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https://youtu.be/-Wycdz3J_RQ
The H3 Launch Vehicle, Japan's new flagship rocket, is about to launch from the Tanegashima Space Center.
By inheriting the high launch success rate and on-time launch rate of the H-IIA Launch Vehicle, H3 will also offer a reliable launch.
We introduce the work of the Tanegashima Space Center, which supports the reliable launch.
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https://youtu.be/J1H-IndX0ek
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LE-9 acceptance test for H3 test flight #2
https://www.youtube.com/watch?v=oFZGMdzsxk0
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https://twitter.com/tnsc_jaxa/status/1615900646678630400
🟠 VOS
#H3ロケットの軌跡
The work to stand the rocket on the mobile launch pad (ML5) in the large rocket assembly building (VAB) is called VOS-Vehicle On Stand 🧍🚀
It is a work to carefully assemble the rocket lifted by a crane 🧑🔧
In H3 test machine No. 1, disassembly work (reverse VOS) was also performed, so VOS was performed 3 times in total 👀💫
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https://twitter.com/tnsc_jaxa/status/1617365996595212288
🟠 SRB-3 binding task
#H3ロケットの軌跡
Work to connect the solid rocket booster (SRB-3) to the 1st stage fuselage was done twice 🧑🔧
SRB-3 once removed from the fuselage after a "cryogenic inspection" called F-0 🔥
With messages of support from everyone, it was re-attached to the 1st stage on December 26, 2022 🥹💫
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https://twitter.com/tnsc_jaxa/status/1620285055418646530
🟠 whole machine vibration test (modal survey)
#H3ロケットの軌跡
The whole machine vibration test is a test to shake the rocket and check how it moves 🚀
Considering the characteristics of the shaking, "how to control the rocket" is examined, so it is a very important thing that affects the entire system 👀
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H3:
https://youtu.be/lUnMkLFKs6s
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https://twitter.com/tnsc_jaxa/status/1624937009344307201
🟠 LE-9 engine installation
#H3ロケットの軌跡
Newly developed H3 rocket first stage engine "LE-9"
The LE-9 engine for the flight of the H3 rocket test machine No. 1 has undergone an acceptance combustion test (AT: Acceptance Test)
1st unit ☝️ on September 21, 2022
Second on October 11, 2022 ✌️
was attached to the 1st stage fuselage 🔥
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Keep testing LE-9 diligently. 3D molded injector for launch 2 and following. (1st test of 5)
https://www.rocket.jaxa.jp/rocket/engine/le9/2023/230220.html
https://www.rocket.jaxa.jp/rocket/engine/le9/2023/230221.html
Google translate:
Results of the first LE-9 engine combustion test for the H3 rocket (blade vibration measurement test/technical data acquisition test)
February 24, 2023 Japan
Aerospace Exploration Agency
We would like to inform you of the results of the first LE-9 engine combustion test that was announced on February 20, 2023.
test day: February 21, 2023
Testing location :Japan Aerospace Exploration Agency Tanegashima Space Center (Kagoshima Prefecture)
Test purpose: Confirmation of vibration response of turbopump blades and acquisition of technical data for 3D molded injectors to verify countermeasures against LE-9 engine issues for H3 rocket test vehicle No. 2 and beyond.
...
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Apparently there's a RFP for H-3 rideshares out now.
Not sure if this is the right link or not though
https://aerospacebiz.jaxa.jp/jaxa-smash/call-for-mission2/ (https://aerospacebiz.jaxa.jp/jaxa-smash/call-for-mission2/)
EDIT
This seems to be the right URL...
https://aerospacebiz.jaxa.jp/topics/koubo/h3rfi_20230605/ (https://aerospacebiz.jaxa.jp/topics/koubo/h3rfi_20230605/)
Though apparently the deadline was so tight you basically had to have a satellite mostly already finished or ready to go to qualify...
There should be an announcement soon of who is gonna ride.
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Looks like 2 rideshares announced for H-3 test flight 2 just now
TIRSAT, a 3U sat, and CE-SAT-1E (previously rumored to have been scheduled to ride SpaceX Transporter 9 along with it's sister sat CE-SAT-1D)
https://news.yahoo.co.jp/byline/akiyamaayano/20230627-00355449 (https://news.yahoo.co.jp/byline/akiyamaayano/20230627-00355449)
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Shown in video:
MHI LE-5B-3 (Sea Level nozzle version) testing for H3 RTF:
https://youtu.be/InIBQ_k-rUA?si=9mcVGC-a7oJNK6LC
Not shown in video:
Early R&D Design work for proposed follow on upgrade LE-5C(-1).
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JAXA H3 RTF Update (in Japanese) Livestream:
https://youtu.be/0kpDOcUfpEg?si=Fkd4mmXyh8cmnwON
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https://youtu.be/0WoYWrNGfoQ