H-I: Difference between revisions

	H-I rocket
Function	Carrier rocket
Manufacturer	McDonnell Douglas (design); Mitsubishi Heavy Industries (production)
Country of origin	Japan (production); United States (design)
Size
Height	42 metres (138 ft)
Diameter	2.44 metres (8.0 ft)
Mass	142,260 kilograms (313,630 lb)
Stages	2 or 3
Capacity
Payload to LEO
Mass	3,200 kilograms (7,100 lb)
Payload to GTO
Mass	1,100 kilograms (2,400 lb)
Associated rockets
Family	Thor
Comparable	Delta 3000, PSLV
Launch history
Status	Retired
Launch sites	LA-N, Tanegashima
Total launches	9
Success(es)	9
First flight	12 August 1986
Last flight	11 February 1992
Boosters – Castor 2
No. boosters	6 or 9
Powered by	1 TX-354-3
Maximum thrust	258.9 kilonewtons (58,200 lbf)
Specific impulse	262 sec
Burn time	37 seconds
Propellant	Solid
First stage – Thor-ELT
Powered by	1 MB-3-3
Maximum thrust	866.7 kilonewtons (194,800 lbf)
Specific impulse	290 sec
Burn time	270 seconds
Propellant	RP-1/LOX
Second stage
Powered by	1 LE-5
Maximum thrust	102.9 kilonewtons (23,100 lbf)
Specific impulse	450 sec
Burn time	370 seconds
Propellant	LH2/LOX
Third stage (optional)
Powered by	1 UM-129A
Maximum thrust	77.4 kilonewtons (17,400 lbf)
Specific impulse	291 sec
Burn time	68 seconds
Propellant	Solid
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Revision as of 14:59, 26 October 2018

The H–I or H–1 was a Japanese liquid-fuelled carrier rocket, consisting of a licence-produced American first stage and set of booster rockets, and all-Japanese upper stages. It was launched nine times between 1986 and 1992. It replaced the N-II, and was subsequently replaced by the H–2, 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. On launches to Geosynchronous transfer orbits, 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 2 SRMs were used as booster rockets.

Launch history

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

References

^ 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 22 May 2013. Retrieved 31 August 2008. {{cite web}}: Unknown parameter |deadurl= ignored (|url-status= suggested) (help)
McDowell, Jonathan. "Thor". Orbital and Suborbital Launch Database. Jonathan's Space Report. Retrieved 31 August 2008.
Krebs, Gunter. "H-1". Gunter's Space Page. Retrieved 31 August 2008.

This rocketry article is a stub. You can help Wikipedia by expanding it.

[1] Japan's H–1 and H–2 rockets, Air & Space/Smithsonian, February/March 1987, p. 19

[1]

@@ Line 1: / Line 1: @@
+{{Infobox Rocket
-This is what bullsHET look
+|image         = H-I.svg
+|caption       = H-I rocket
+|imsize        = 75
+|function      = [[Carrier rocket]]
+|manufacturer  = [[McDonnell Douglas]] (design)<br>[[Mitsubishi Heavy Industries]] (production)
+|country-origin= Japan (production)<br>United States (design)
+|height        = {{convert|42|m|ft}}
+|diameter      = {{convert|2.44|m|ft}}
+|mass          = {{convert|142260|kg|lb}}
+|stages        = 2 or 3
+|capacities    =
+{{Infobox Rocket/Payload
+|location      = [[Low Earth orbit|LEO]]
+|kilos         = {{convert|3200|kg|lb}}
+}}
+{{Infobox Rocket/Payload
+|location      = [[Geosynchronous transfer orbit|GTO]]
+|kilos         = {{convert|1100|kg|lb}}
+}}
+|family        = [[Thor (rocket)|Thor]]
+|comparable    = [[Delta 3000]], [[PSLV]]
+|status        = Retired
+|sites         = LA-N, [[Tanegashima]]
+|launches      = 9
+|success       = 9
+|first         = 12 August 1986
+|last          = 11 February 1992
+|stagedata     =
+{{Infobox Rocket/Stage
+|type          = booster
+|name          = [[Castor (rocket)|Castor 2]]
+|number        = 6 or 9
+|engines       = 1 [[TX-354-3]]
+|thrust        = {{convert|258.9|kN|lbf}}
+|SI            = 262 sec
+|burntime      = 37 seconds
+|fuel          = [[Solid rocket|Solid]]
+}}
+{{Infobox Rocket/Stage
+|type          = stage
+|stageno       = First
+|name          = [[Thor (rocket)|Thor-ELT]]
+|engines       = 1 [[MB-3-3]]
+|thrust        = {{convert|866.7|kN|lbf}}
+|SI            = 290 sec
+|burntime      = 270 seconds
+|fuel          = [[RP-1]]/[[LOX]]
+}}
+{{Infobox Rocket/Stage
+|type         = stage
+|stageno      = Second
+|engines      = 1 [[LE-5]]
+|thrust       = {{convert|102.9|kN|lbf}}
+|SI           = 450 sec
+|burntime     = 370 seconds
+|fuel         = [[LH2]]/[[LOX]]
+}}
+{{Infobox Rocket/Stage
+|type         = stage
+|stageno      = Third
+|diff         = optional
+|engines      = 1 [[UM-129A]]
+|thrust       = {{convert|77.4|kN|lbf}}
+|SI           = 291 sec
+|burntime     = 68 seconds
+|fuel         = [[solid rocket|Solid]]
+}}
+}}
+The '''H–I''' or '''H–1''' was a Japanese [[liquid-fuel rocket|liquid-fuelled]] [[carrier rocket]], consisting of a licence-produced 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 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.
+[[File:Delta launches OSO 8.jpg|200px|thumb|The American Thor-ELT was used for the H-I.]]
 ==Launch history==

v t e Orbital launch systems
List of orbital launch systems Comparison of orbital launch systems
Current	Angara 1.2 A5 Ariane 6 Atlas V Ceres 1 1S Chollima-1 Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Gravity-1 GSLV H-IIA H3 Hyperbola-1 Jielong 1 3 KAIROS^† Kaituozhe 2 Kinetica 1 Kuaizhou 1 1A 11 Long March 2C 2D 2F 3A 3B/E 3C 4B 4C 5 5B 6 6A 7 7A 8 11 11H LVM3 Minotaur I IV V C Nuri OS-M1^† Pegasus XL Proton-M PSLV Qaem 100 Qased Shavit 2 Simorgh SLS Block 1 Soyuz-2 2.1a / STA 2.1b / STB 2-1v SSLV Starship Tianlong-2 Unha Vega C Vulcan Centaur Zhuque 2
In development	Antares 330 Bloostar Cyclone-4M Deca Epsilon S Eris Gravity-2 Hyperbola-2 Irtysh Kuaizhou 21 31 Long March 9 10 12 Miura 5 MLV Neutron New Glenn New Line 1 NGLV Nova OS-M 2 4 Orbex Prime Pallas-1 Red Dwarf SLS Block 1B Block 2 Soyuz-7 Terran R Tianlong-3 VLM Vega E Zero Zhuque 3 Zuljanah
Retired	Antares 110 120 130^† 230 230+ Ariane 1 2 3 4 5 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able^† Agena Centaur Black Arrow Conestoga^† Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Diamant Dnepr Energia Epsilon Europa I^† II^† Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" Feng Bao 1 GSLV Mk I H-I H-II H-IIB Juno I Juno II Kaituozhe-1 Kosmos original 1 2/2I 3 3M Lambda 4S LauncherOne Long March 1 1D^† 2A 2E 3 3B 4A Mu 4S 3C 3H 3S 3SII V N1^† N-I N-II Naro-1 Paektusan^† Pilot-2^† R-7 Luna Molniya M L Polyot Soyuz original FG L M U U2 Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna^† Rocket 3 RS1^† Safir 1 1A 1B Saturn I IB V Scout X-1 Blue Scout II^† X-2^† X-2M X-3 X-3M X-4 X-2B^† B A B-1 D-1 A-1 E-1 F-1 G-1 Shavit original 1 SLV Space Shuttle SPARK^† Sparta SS-520 Start-1 Terran 1^† Thor Able Ablestar 1 2 Agena A B D Burner 1 2 Delta DSV-2U Thorad-Agena SLV-2G SLV-2H Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon R-36-O original 2 3 Universal Rocket UR-500 Proton Proton-K Rokot Strela Vanguard Vega original VLS-1^† Zenit 2 2M 2FG 3SL 3SLB 3F Zhuque 1^†
Classes	Sounding rocket Small-lift launch vehicle Medium-lift launch vehicle Heavy-lift launch vehicle Super heavy-lift launch vehicle
This Template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future Symbol ^† indicates past or current rockets that attempted orbital launches but never succeeded (never did or has yet to perform a successful orbital launch)

Revision as of 14:59, 26 October 2018

Launch history

See also

References