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{{short description|Japanese liquid-fuelled carrier rocket}}
{{Infobox Rocket
{{Infobox Rocket
|image = H-I.svg
|image = H-I.svg
|caption = H-I rocket
|caption = H-I rocket
|imsize = 75
|function = [[Medium-lift launch vehicle]]
|manufacturer = {{Indented plainlist|
|function = [[Carrier rocket]]
|manufacturer = [[McDonnell Douglas]] (design)<br>[[Mitsubishi Heavy Industries]] (production)
* [[Mitsubishi Heavy Industries]] (production)
* [[McDonnell Douglas]] (design)
|country-origin= {{JPN}} (production)<br>{{USA}} (design)
}}
|height = {{convert|42|m|ft}}
|country-origin= {{Indented plainlist|
|diameter = {{convert|2.44|m|ft}}
* Japan (production)
|mass = {{convert|142260|kg|lb}}
* United States (design)
}}
|height = {{cvt|42|m}}
|diameter = {{cvt|2.44|m}}
|mass = {{cvt|142260|kg}}
|stages = 2 or 3
|stages = 2 or 3
|capacities =
|capacities =
{{Infobox Rocket/Payload
{{Infobox Rocket/Payload
|location = [[Low Earth orbit|LEO]]
|location = [[Low Earth orbit|LEO]]
|kilos = {{convert|3200|kg|lb}}
|mass = {{cvt|3200|kg}}
}}
}}
{{Infobox Rocket/Payload
{{Infobox Rocket/Payload
|location = [[Geosynchronous transfer orbit|GTO]]
|location = [[Geosynchronous transfer orbit|GTO]]
|kilos = {{convert|1100|kg|lb}}
|mass = {{cvt|1100|kg}}
}}
}}
|family = [[Thor (rocket)|Thor]]
|family = [[Thor (rocket)|Thor]]
|comparable = [[Delta 3000]], [[PSLV]]
|comparable = [[Delta 3000]], [[PSLV]]
|status = Retired
|status = Retired
|sites = LA-N, [[Tanegashima]]
|sites = [[Tanegashima Space Center|Tanegashima]], [[Osaki Launch Complex|Osaki]]
|launches = 9
|launches = 9
|success = 9
|success = 9
Line 30: Line 36:
{{Infobox Rocket/Stage
{{Infobox Rocket/Stage
|type = booster
|type = booster
|solid = yes
|name = [[Castor (rocket)|Castor 2]]
|name = [[Castor (rocket)|Castor 2]]
|number = 6 or 9
|number = 6 or 9
|engines = 1 [[TX-354-3]]
|engines = 1 × [[TX-354-3]]
|thrust = {{convert|258.9|kN|lbf}}
|thrust = {{cvt|258.9|kN}}
|SI = 262 sec
|SI = {{cvt|262|isp}}
|burntime = 37 seconds
|burntime = 37 seconds
|fuel = [[Solid rocket|Solid]]
|fuel = [[Hydroxyl-terminated polybutadiene|HTPB]]/Al
}}
}}
{{Infobox Rocket/Stage
{{Infobox Rocket/Stage
Line 42: Line 49:
|stageno = First
|stageno = First
|name = [[Thor (rocket)|Thor-ELT]]
|name = [[Thor (rocket)|Thor-ELT]]
|engines = 1 [[MB-3-3]]
|engines = 1 × [[MB-3-3]]
|thrust = {{convert|866.7|kN|lbf}}
|thrust = {{cvt|866.7|kN}}
|SI = 290 sec
|SI = {{cvt|290|isp}}
|burntime = 270 seconds
|burntime = 270 seconds
|fuel = [[RP-1]]/[[LOX]]
|fuel = [[RP-1]]/[[LOX]]
Line 51: Line 58:
|type = stage
|type = stage
|stageno = Second
|stageno = Second
|engines = 1 [[LE-5]]
|engines = 1 × [[LE-5]]
|thrust = {{convert|102.9|kN|lbf}}
|thrust = {{cvt|102.9|kN}}
|SI = 450 sec
|SI = {{cvt|450|isp}}
|burntime = 370 seconds
|burntime = 370 seconds
|fuel = [[LH2]]/[[LOX]]
|fuel = [[LH2]]/[[LOX]]
Line 61: Line 68:
|stageno = Third
|stageno = Third
|diff = optional
|diff = optional
|engines = 1 [[UM-129A]]
|engines = 1 × [[UM-129A]]
|thrust = {{convert|77.4|kN|lbf}}
|thrust = {{cvt|77.4|kN}}
|SI = 291 sec
|SI = {{cvt|291|isp}}
|burntime = 68 seconds
|burntime = 68 seconds
|fuel = [[solid rocket|Solid]]
|fuel = [[solid rocket|Solid]]
}}
}}
|derived_from=[[N-II (rocket)|N-II]]|derivatives=[[H-II]]}}
}}
The '''H–I''' or '''H–1''' was a [[Japan]]ese [[liquid-fuel rocket|liquid-fuelled]] [[carrier rocket]], consisting of a licence-produced [[United States|American]] first stage and set of [[booster rocket]]s, and all-Japanese upper stages. It was launched nine times between 1986 and 1992. It replaced the [[N-II (rocket)|N-II]], and was subsequently replaced by the [[H-II|H–2]], which used the same upper stages with a Japanese first stage.
The '''H–I''' ('''H–1''') was a Japanese [[medium-lift launch vehicle]], consisting of a licence-produced American first stage and set of [[booster rocket]]s, and all-Japanese upper stages. The H in the name represented the use of liquid hydrogen fuel in the second stage. It was launched nine times between 1986 and 1992. It replaced the [[N-II (rocket)|N-II]], and was subsequently replaced by the [[H-II]], which used the same upper stages with a Japanese first stage.


The first stage of the H–I was a licence-built version of the [[Thor (rocket)|Thor-ELT]], which was originally constructed for the US [[Delta 1000]] rocket. The stage had already been produced under licence in Japan for the [[N-I (rocket)|N-I]] and N-II rockets. The second stage was entirely Japanese, using an [[LE-5]] engine. On launches to [[Geosynchronous transfer orbit]]s, a [[Nissan]]–built [[UM-129A]] solid motor was used as a third stage. Depending on the mass of the payload, either six or nine US [[Castor (rocket)|Castor 2]] SRMs were used as [[booster rocket]]s.
The first stage of the H–I was a licence-built version of the [[Thor (rocket)|Thor-ELT]], which was originally constructed for the US [[Delta 1000]] rocket. The stage had already been produced under licence in Japan for the [[N-I (rocket)|N-I]] and N-II rockets. The second stage was entirely Japanese, using an [[LE-5]] engine, the first rocket engine in Japan to use a [[cryogenic fuel]]. On launches to [[Geosynchronous transfer orbit]]s, a [[Nissan]]–built [[UM-69A]] solid motor was used as a third stage. Depending on the mass of the payload, either six or nine US [[Castor (rocket)|Castor 2]] SRMs were used as [[booster rocket]]s.


[[File:Delta launches OSO 8.jpg|200px|thumb|The American Thor-ELT was used for the H-I.]]
[[File:Delta launches OSO 8.jpg|200px|thumb|The American Thor-ELT was used for the H-I.]]


==Launch history==
==Launch history==
{| class="wikitable"
{| class="wikitable plainrowheaders"
!Date/Time (GMT)
!S/N
!Payload
!Orbit
!Remarks
|-
|-
! scope="col" | Flight No.
|12 August 1986, 20:45
! scope="col" | Date / time ([[Coordinated Universal Time|UTC]])
|15(F)
! scope="col" | Rocket, <br /> Configuration
|[[Experimental Geodetic Payload|EGP]] ([[Experimental Geodetic Payload|Ajisai]])
! scope="col" | Launch site
|[[Low Earth orbit|LEO]]
! scope="col" | Payload
|9 SRMs, 2 stages
! scope="col" | Payload mass
! scope="col" | Orbit
! scope="col" | Customer
! scope="col" | Launch <br /> outcome
|-
|-
! scope="row" rowspan = 2 style="text-align:center;|15(F)
|27 August 1987, 09:20
| 12 August 1986,<br>20:45
|17(F)
| H-I
|[[ETS-5]] ([[Kiku-5]])
| [[Osaki Launch Complex]]
|[[Geosynchronous transfer orbit|GTO]]
| [[Experimental Geodetic Payload|EGP]] ([[Experimental Geodetic Payload|Ajisai]])
|9 SRMs, 3 stages
|-
|
| [[Low Earth orbit|LEO]]
|19 February 1988, 10:05
|
|18(F)
| {{Success}}
|[[CS-3A]] ([[Sakura-3A]])
|[[Geosynchronous transfer orbit|GTO]]
|9 SRMs, 3 stages
|-
|-
| colspan="8" |9 SRMs, 2 stages
|16 September 1988, 09:59
|19(F)
|[[CS-3B]] ([[Sakura-3B]])
|[[Geosynchronous transfer orbit|GTO]]
|9 SRMs, 3 stages
|-
|-
! scope="row" rowspan = 2 style="text-align:center;|17(F)
|5 September 1989, 19:11
| 27 August 1987,<br>09:20
|20(F)
| H-I
|[[GMS-4]] ([[Himawari-4]])
| [[Osaki Launch Complex]]
|[[Geosynchronous transfer orbit|GTO]]
| [[ETS-5]] ([[Kiku-5]])
|6 SRMs, 3 stages
|
| [[Geosynchronous transfer orbit|GTO]]
|
| {{Success}}
|-
|-
| colspan="8" |9 SRMs, 3 stages
|7 February 1990, 01:33
|-
|21(F)
! scope="row" rowspan = 2 style="text-align:center;|18(F)
|[[MOS-1B]] ([[Momo-1B]])
| 19 February 1988,<br>10:05
|[[Low Earth orbit|LEO]]
| H-I
|9 SRMs, 2 stages
| [[Osaki Launch Complex]]
|-
| [[CS-3A]] ([[Sakura-3A]])
|28 August 1990, 09:05
|
|22(F)
| [[Geosynchronous transfer orbit|GTO]]
|[[BS-3A]] ([[Yuri-3A]])
|
|[[Geosynchronous transfer orbit|GTO]]
| {{Success}}
|9 SRMs, 3 stages
|-
|-
| colspan="8" |9 SRMs, 3 stages
|25 August 1991, 08:40
|-
|23(F)
! scope="row" rowspan = 2 style="text-align:center;|19(F)
|[[BS-3B]] ([[Yuri-3B]])
| 16 September 1988,<br>09:59
|[[Geosynchronous transfer orbit|GTO]]
| H-I
|9 SRMs, 3 stages
| [[Osaki Launch Complex]]
|-
| [[CS-3B]] ([[Sakura-3B]])
|11 February 1992, 01:50
|
|24(F)
| [[Geosynchronous transfer orbit|GTO]]
|[[Japanese Research Satellite 1|JERS-1]] ([[FUYO-1]])
|
|[[Low Earth orbit|LEO]]
| {{Success}}
|9 SRMs, 2 stages
|-
| colspan="8" |9 SRMs, 3 stages
|-
! scope="row" rowspan = 2 style="text-align:center;|20(F)
| 5 September 1989,<br>19:11
| H-I
| [[Osaki Launch Complex]]
| [[GMS-4]] ([[Himawari-4]])
|
| [[Geosynchronous transfer orbit|GTO]]
|
| {{Success}}
|-
| colspan="8" |6 SRMs, 3 stages
|-
! scope="row" rowspan = 2 style="text-align:center;|21(F)
| 7 February 1990,<br>01:33
| H-I
| [[Osaki Launch Complex]]
| [[MOS-1B]] ([[Momo-1B]])
|
| [[Low Earth orbit|LEO]]
|
| {{Success}}
|-
| colspan="8" |9 SRMs, 2 stages
|-
! scope="row" rowspan = 2 style="text-align:center;|22(F)
| 28 August 1990,<br>09:05
| H-I
| [[Osaki Launch Complex]]
| [[BS-3A]] ([[Yuri-3A]])
|
| [[Geosynchronous transfer orbit|GTO]]
|
| {{Success}}
|-
| colspan="8" |9 SRMs, 3 stages
|-
! scope="row" rowspan = 2 style="text-align:center;|23(F)
| 25 August 1991,<br>08:40
| H-I
| [[Osaki Launch Complex]]
| [[BS-3B]] ([[Yuri-3B]])
|
| [[Geosynchronous transfer orbit|GTO]]
|
| {{Success}}
|-
| colspan="8" |9 SRMs, 3 stages
|-
! scope="row" rowspan = 2 style="text-align:center;|24(F)
| 11 February 1992,<br>01:50
| H-I
| [[Osaki Launch Complex]]
| [[Japanese Research Satellite 1|JERS-1]] ([[FUYO-1]])
|
| [[Low Earth orbit|LEO]]
|
| {{Success}}
|-
| colspan="8" |9 SRMs, 2 stages
|-
|-
|}
|}


When the H–1 was announced in 1986, company representative Tsuguo Tatakawe clarified that it would only be used to launch indigenous (i.e. Japanese) payloads, that only two launches per year could be mounted, and that the launch window consisted of a four-month period in which Japanese fishing fleets were not active (the falling launch boosters may damage fishing nets in the ocean waters).<ref>''Japan's H–1 and H–2 rockets'', [[Air & Space/Smithsonian]], February/March 1987, p. 19</ref>
When the H–1 was announced in 1986, company representative Tsuguo Tatakawe clarified that it would only be used to launch indigenous (i.e. Japanese) payloads, that only two launches per year could be mounted, and that the launch window consisted of a four-month period in which Japanese fishing fleets were not active (the falling launch boosters may damage fishing nets in the ocean waters).<ref>''Japan's H–1 and H–2 rockets'', [[Air & Space/Smithsonian]], February/March 1987, p. 19</ref>

==See also==
==See also==
*[[Delta rocket]]
*[[Delta rocket]]
Line 150: Line 215:
==References==
==References==
{{reflist}}
{{reflist}}
*{{cite web|url=http://www.astronautix.com/lvs/delta.htm|title=Delta|first=Mark|last=Wade|publisher=Encyclopedia Astronautica|accessdate=31 August 2008}}
*{{cite web|url=http://www.astronautix.com/lvs/delta.htm|title=Delta|first=Mark|last=Wade|publisher=[[Encyclopedia Astronautica]]|access-date=31 August 2008|url-status=dead|archive-url=https://web.archive.org/web/20130817180906/http://astronautix.com/lvs/delta.htm|archive-date=17 August 2013}}
*{{cite web|url=http://planet4589.org/space/lvdb/launch/Thor|title=Thor|first=Jonathan|last=McDowell|work=Orbital and Suborbital Launch Database|publisher=Jonathan's Space Report|accessdate=31 August 2008}}
*{{cite web|url=http://planet4589.org/space/lvdb/launch/Thor|title=Thor|first=Jonathan|last=McDowell|work=Orbital and Suborbital Launch Database|publisher=[[Jonathan's Space Report]]|access-date=31 August 2008|archive-date=1 August 2020|archive-url=https://web.archive.org/web/20200801135201/http://planet4589.org/space/lvdb/launch/Thor|url-status=dead}}
*{{cite web|url=http://space.skyrocket.de/doc_lau/h-1.htm|title=H-1|first=Gunter|last=Krebs|publisher=Gunter's Space Page|accessdate=31 August 2008}}
*{{cite web|url=http://space.skyrocket.de/doc_lau/h-1.htm|title=H-1|first=Gunter|last=Krebs|publisher=Gunter's Space Page|access-date=31 August 2008}}


{{Expendable launch systems}}
{{Expendable launch systems}}
Line 158: Line 223:
{{Mitsubishi Heavy Industries}}
{{Mitsubishi Heavy Industries}}
{{Thor and Delta rockets}}
{{Thor and Delta rockets}}

[[Category:Space launch vehicles of Japan]]
[[Category:Mitsubishi Heavy Industries space launch vehicles]]
[[Category:Vehicles introduced in 1986]]
[[Category:Thor (rocket family)]]
[[Category:Japan–United States relations]]



{{rocket-stub}}
{{rocket-stub}}

Latest revision as of 04:57, 6 September 2024

H-I rocket
FunctionMedium-lift launch vehicle
Manufacturer
Country of origin
  • Japan (production)
  • United States (design)
Size
Height42 m (138 ft)
Diameter2.44 m (8 ft 0 in)
Mass142,260 kg (313,630 lb)
Stages2 or 3
Capacity
Payload to LEO
Mass3,200 kg (7,100 lb)
Payload to GTO
Mass1,100 kg (2,400 lb)
Associated rockets
FamilyThor
Based onN-II
Derivative workH-II
ComparableDelta 3000, PSLV
Launch history
StatusRetired
Launch sitesTanegashima, Osaki
Total launches9
Success(es)9
First flight12 August 1986
Last flight11 February 1992
Boosters – Castor 2
No. boosters6 or 9
Powered by1 × TX-354-3
Maximum thrust258.9 kN (58,200 lbf)
Specific impulse262 s (2.57 km/s)
Burn time37 seconds
PropellantHTPB/Al
First stage – Thor-ELT
Powered by1 × MB-3-3
Maximum thrust866.7 kN (194,800 lbf)
Specific impulse290 s (2.8 km/s)
Burn time270 seconds
PropellantRP-1/LOX
Second stage
Powered by1 × LE-5
Maximum thrust102.9 kN (23,100 lbf)
Specific impulse450 s (4.4 km/s)
Burn time370 seconds
PropellantLH2/LOX
Third stage (optional)
Powered by1 × UM-129A
Maximum thrust77.4 kN (17,400 lbf)
Specific impulse291 s (2.85 km/s)
Burn time68 seconds
PropellantSolid
[edit on Wikidata]

The H–I (H–1) was a Japanese medium-lift launch vehicle, consisting of a licence-produced American first stage and set of booster rockets, and all-Japanese upper stages. The H in the name represented the use of liquid hydrogen fuel in the second stage. It was launched nine times between 1986 and 1992. It replaced the N-II, and was subsequently replaced by the H-II, which used the same upper stages with a Japanese first stage.

The first stage of the H–I was a licence-built version of the Thor-ELT, which was originally constructed for the US Delta 1000 rocket. The stage had already been produced under licence in Japan for the N-I and N-II rockets. The second stage was entirely Japanese, using an LE-5 engine, the first rocket engine in Japan to use a cryogenic fuel. On launches to Geosynchronous transfer orbits, a Nissan–built UM-69A solid motor was used as a third stage. Depending on the mass of the payload, either six or nine US Castor 2 SRMs were used as booster rockets.

The American Thor-ELT was used for the H-I.

Launch history

[edit]
Flight No. Date / time (UTC) Rocket,
Configuration 		Launch site Payload Payload mass Orbit Customer Launch
outcome
15(F) 12 August 1986,
20:45 		H-I Osaki Launch Complex EGP (Ajisai) LEO Success
9 SRMs, 2 stages
17(F) 27 August 1987,
09:20 		H-I Osaki Launch Complex ETS-5 (Kiku-5) GTO Success
9 SRMs, 3 stages
18(F) 19 February 1988,
10:05 		H-I Osaki Launch Complex CS-3A (Sakura-3A) GTO Success
9 SRMs, 3 stages
19(F) 16 September 1988,
09:59 		H-I Osaki Launch Complex CS-3B (Sakura-3B) GTO Success
9 SRMs, 3 stages
20(F) 5 September 1989,
19:11 		H-I Osaki Launch Complex GMS-4 (Himawari-4) GTO Success
6 SRMs, 3 stages
21(F) 7 February 1990,
01:33 		H-I Osaki Launch Complex MOS-1B (Momo-1B) LEO Success
9 SRMs, 2 stages
22(F) 28 August 1990,
09:05 		H-I Osaki Launch Complex BS-3A (Yuri-3A) GTO Success
9 SRMs, 3 stages
23(F) 25 August 1991,
08:40 		H-I Osaki Launch Complex BS-3B (Yuri-3B) GTO Success
9 SRMs, 3 stages
24(F) 11 February 1992,
01:50 		H-I Osaki Launch Complex JERS-1 (FUYO-1) LEO Success
9 SRMs, 2 stages

When the H–1 was announced in 1986, company representative Tsuguo Tatakawe clarified that it would only be used to launch indigenous (i.e. Japanese) payloads, that only two launches per year could be mounted, and that the launch window consisted of a four-month period in which Japanese fishing fleets were not active (the falling launch boosters may damage fishing nets in the ocean waters).[1]

See also

[edit]

References

[edit]
  1. ^ Japan's H–1 and H–2 rockets, Air & Space/Smithsonian, February/March 1987, p. 19
  • Wade, Mark. "Delta". Encyclopedia Astronautica. Archived from the original on 17 August 2013. Retrieved 31 August 2008.
  • McDowell, Jonathan. "Thor". Orbital and Suborbital Launch Database. Jonathan's Space Report. Archived from the original on 1 August 2020. Retrieved 31 August 2008.
  • Krebs, Gunter. "H-1". Gunter's Space Page. Retrieved 31 August 2008.


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