H-I: Difference between revisions

	H-I rocket
Function	Medium-lift launch vehicle
Manufacturer	Mitsubishi Heavy Industries (production); McDonnell Douglas (design);
Country of origin	Japan (production); United States (design);
Size
Height	42 m (138 ft)
Diameter	2.44 m (8 ft 0 in)
Mass	142,260 kg (313,630 lb)
Stages	2 or 3
Capacity
Payload to LEO
Mass	3,200 kg (7,100 lb)
Payload to GTO
Mass	1,100 kg (2,400 lb)
Associated rockets
Family	Thor
Based on	N-II
Derivative work	H-II
Comparable	Delta 3000, PSLV
Launch history
Status	Retired
Launch sites	Tanegashima, Osaki
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 kN (58,200 lbf)
Specific impulse	262 s (2.57 km/s)
Burn time	37 seconds
Propellant	HTPB/Al
First stage – Thor-ELT
Powered by	1 × MB-3-3
Maximum thrust	866.7 kN (194,800 lbf)
Specific impulse	290 s (2.8 km/s)
Burn time	270 seconds
Propellant	RP-1/LOX
Second stage
Powered by	1 × LE-5
Maximum thrust	102.9 kN (23,100 lbf)
Specific impulse	450 s (4.4 km/s)
Burn time	370 seconds
Propellant	LH2/LOX
Third stage (optional)
Powered by	1 × UM-129A
Maximum thrust	77.4 kN (17,400 lbf)
Specific impulse	291 s (2.85 km/s)
Burn time	68 seconds
Propellant	Solid
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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.

Launch history

Flight No.	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 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.

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: @@
+{{short description|Japanese liquid-fuelled carrier rocket}}
 {{Infobox Rocket
 |image         = H-I.svg
 |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= Japan (production)<br>United States (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
 |capacities    =
 {{Infobox Rocket/Payload
 |location      = [[Low Earth orbit|LEO]]
-|kilos         = {{convert|3200|kg|lb}}
+|mass          = {{cvt|3200|kg}}
 }}
 {{Infobox Rocket/Payload
 |location      = [[Geosynchronous transfer orbit|GTO]]
-|kilos         = {{convert|1100|kg|lb}}
+|mass          = {{cvt|1100|kg}}
 }}
 |family        = [[Thor (rocket)|Thor]]
 |comparable    = [[Delta 3000]], [[PSLV]]
 |status        = Retired
-|sites         = LA-N, [[Tanegashima]]
+|sites         = [[Tanegashima Space Center|Tanegashima]], [[Osaki Launch Complex|Osaki]]
 |launches      = 9
 |success       = 9
@@ Line 30: / Line 36: @@
 {{Infobox Rocket/Stage
 |type          = booster
+|solid         = yes
 |name          = [[Castor (rocket)|Castor 2]]
 |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
-|fuel          = [[Solid rocket|Solid]]
+|fuel          = [[Hydroxyl-terminated polybutadiene|HTPB]]/Al
 }}
 {{Infobox Rocket/Stage
@@ Line 42: / Line 49: @@
 |stageno       = First
 |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
 |fuel          = [[RP-1]]/[[LOX]]
@@ Line 51: / Line 58: @@
 |type         = stage
 |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
 |fuel         = [[LH2]]/[[LOX]]
@@ Line 61: / Line 68: @@
 |stageno      = Third
 |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
 |fuel         = [[solid rocket|Solid]]
 }}
+|derived_from=[[N-II (rocket)|N-II]]|derivatives=[[H-II]]}}
-}}
-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 '''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.]]
 ==Launch history==
-{{main|List of H-I and H-II launches}}
 {| class="wikitable plainrowheaders"
 |-
-! scope="col" | Flight №
+! scope="col" | Flight No.
 ! scope="col" | Date / time ([[Coordinated Universal Time|UTC]])
 ! scope="col" | Rocket, <br /> Configuration
@@ Line 99: / Line 104: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 2 stages
+| colspan="8" |9 SRMs, 2 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|17(F)
@@ Line 111: / Line 116: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 3 stages
+| colspan="8" |9 SRMs, 3 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|18(F)
@@ Line 123: / Line 128: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 3 stages
+| colspan="8" |9 SRMs, 3 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|19(F)
@@ Line 135: / Line 140: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 3 stages
+| colspan="8" |9 SRMs, 3 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|20(F)
@@ Line 147: / Line 152: @@
 | {{Success}}
 |-
-| colspan=9 |6 SRMs, 3 stages
+| colspan="8" |6 SRMs, 3 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|21(F)
@@ Line 159: / Line 164: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 2 stages
+| colspan="8" |9 SRMs, 2 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|22(F)
@@ Line 171: / Line 176: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 3 stages
+| colspan="8" |9 SRMs, 3 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|23(F)
@@ Line 183: / Line 188: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 3 stages
+| colspan="8" |9 SRMs, 3 stages
 |-
 ! scope="row" rowspan = 2 style="text-align:center;|24(F)
@@ Line 195: / Line 200: @@
 | {{Success}}
 |-
-| colspan=9 |9 SRMs, 2 stages
+| 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>
+==See also==
+*[[Delta rocket]]
-NO
+*[[H-II]]
+*[[H-IIA]]
+*[[PGM-17 Thor]]
+* [[Comparison of orbital launchers families]]
+* [[Comparison of orbital launch systems]]
 ==References==
 {{reflist}}
-*{{cite web|url=http://www.astronautix.com/lvs/delta.htm|title=Delta|first=Mark|last=Wade|publisher=[[Encyclopedia Astronautica]]|accessdate=31 August 2008|deadurl=yes|archiveurl=https://www.webcitation.org/6GnQRIrKc?url=http://www.astronautix.com/lvs/delta.htm|archivedate=22 May 2013|df=}}
+*{{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}}
@@ Line 217: / Line 227: @@
 [[Category:Vehicles introduced in 1986]]
 [[Category:Thor (rocket family)]]
+[[Category:Japan–United States relations]]

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)