J-I: Difference between revisions
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[[File:J-I rocket..svg|thumb|50px|J-I]] |
[[File:J-I rocket..svg|thumb|50px|J-I]] |
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The '''J-I''' was a [[Solid-fuel rocket]] expendable launch vehicle developed by the [[National Space Development Agency of Japan]] and the [[Institute of Space and Astronautical Science]]. In an attempt to reduce development costs, it used the [[solid rocket booster]] from the [[H-II]] as the first stage, and the upper stages of the [[Mu (rocket family)|M-3SII]].<ref>{{cite web|url=http://www.jaxa.jp/projects/rockets/j1/index_e.html|title=J-I Launch Vehicle|date=2007|publisher=[[Japan Aerospace Exploration Agency]]}}</ref> It flew only once |
The '''J-I''' was a [[Solid-fuel rocket]] expendable launch vehicle developed by the [[National Space Development Agency of Japan]] and the [[Institute of Space and Astronautical Science]]. In an attempt to reduce development costs, it used the [[solid rocket booster]] from the [[H-II]] as the first stage, and the upper stages of the [[Mu (rocket family)|M-3SII]].<ref>{{cite web|url=http://www.jaxa.jp/projects/rockets/j1/index_e.html|title=J-I Launch Vehicle|date=2007|publisher=[[Japan Aerospace Exploration Agency]]|access-date=2009-05-19|archive-date=2012-08-18|archive-url=https://web.archive.org/web/20120818072733/http://www.jaxa.jp/projects/rockets/j1/index_e.html|url-status=dead}}</ref> It flew only once on a suborbital flight taking place 11 February 1996 UTC from [[Tanegashima Space Center]] pad LA-N, in a partial configuration, to launch the demonstrator [[HYFLEX]]. The vehicle never flew in the final orbital capability configuration, which should have launched the [[OICETS]] satellite (OICETS was launched on a Russian [[R-36 (missile)|R-36MUTTH]] [[Intercontinental ballistic missile]]-based [[Dnepr (rocket)|Dnepr]] rocket instead). |
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On the |
On the HYFLEX mission a load of 1,054 kg was launched 1,300 km downrange. Apogee was 110km; the HYFLEX payload achieved speed of approximately 3.8 km/s. |
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==See also== |
==See also== |
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==External links== |
==External links== |
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* {{cite web|title=J-I Launch Vehicle|publisher=[[Japan Aerospace Exploration Agency]]|url=http://www.jaxa.jp/projects/rockets/j1/index_e.html}} |
* {{cite web|title=J-I Launch Vehicle|publisher=[[Japan Aerospace Exploration Agency]]|url=http://www.jaxa.jp/projects/rockets/j1/index_e.html|access-date=2009-05-19|archive-date=2012-08-18|archive-url=https://web.archive.org/web/20120818072733/http://www.jaxa.jp/projects/rockets/j1/index_e.html|url-status=dead}} |
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* {{cite web|title=Hypersonic Flight Experiment "HYFLEX"|publisher=Japan Aerospace Exploration Agency|url=http://www.jaxa.jp/projects/rockets/hyflex/index_e.html}} |
* {{cite web|title=Hypersonic Flight Experiment "HYFLEX"|publisher=Japan Aerospace Exploration Agency|url=http://www.jaxa.jp/projects/rockets/hyflex/index_e.html|access-date=2011-11-15|archive-date=2013-09-09|archive-url=https://web.archive.org/web/20130909222414/http://www.jaxa.jp/projects/rockets/hyflex/index_e.html|url-status=dead}} |
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{{Expendable launch systems}} |
{{Expendable launch systems}} |
Latest revision as of 22:32, 14 February 2023
This article needs additional citations for verification. (September 2014) |
![](http://upload.wikimedia.org/wikipedia/commons/thumb/0/06/J-I_rocket..svg/50px-J-I_rocket..svg.png)
The J-I was a Solid-fuel rocket expendable launch vehicle developed by the National Space Development Agency of Japan and the Institute of Space and Astronautical Science. In an attempt to reduce development costs, it used the solid rocket booster from the H-II as the first stage, and the upper stages of the M-3SII.[1] It flew only once on a suborbital flight taking place 11 February 1996 UTC from Tanegashima Space Center pad LA-N, in a partial configuration, to launch the demonstrator HYFLEX. The vehicle never flew in the final orbital capability configuration, which should have launched the OICETS satellite (OICETS was launched on a Russian R-36MUTTH Intercontinental ballistic missile-based Dnepr rocket instead).
On the HYFLEX mission a load of 1,054 kg was launched 1,300 km downrange. Apogee was 110km; the HYFLEX payload achieved speed of approximately 3.8 km/s.
See also
[edit]References
[edit]- ^ "J-I Launch Vehicle". Japan Aerospace Exploration Agency. 2007. Archived from the original on 2012-08-18. Retrieved 2009-05-19.
External links
[edit]- "J-I Launch Vehicle". Japan Aerospace Exploration Agency. Archived from the original on 2012-08-18. Retrieved 2009-05-19.
- "Hypersonic Flight Experiment "HYFLEX"". Japan Aerospace Exploration Agency. Archived from the original on 2013-09-09. Retrieved 2011-11-15.