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'''Delta II''' adalah sistem peluncuran luar angkasa yang didesain dan dibangun oleh [[McDonnell Douglas]]. Delta II adalah bagian dari keluarga [[roket Delta]] dan telah beroperasi sejak tahun 1989. Kendaraan Delta II meliputi Delta 6000 yang sudah tidak beroperasi, Delta 7000, dan dua varian 7000 (ringan dan berat). Roket Delta II nantinya dibangun oleh [[Boeing Integrated Defense Systems]] hingga produksi Delta II menjadi tanggung jawab [[United Launch Alliance]] (ULA) pada tanggal 1 Desember 2006.<ref>[http://www.comspacewatch.com/news/viewpr.html?pid=21394 United Launch Alliance Transaction completed]</ref><ref>[http://www.boeing.com/defense-space/space/bls/deltaHistory.html Delta rocket history], Boeing. Accessed 14 June 2008.</ref>
{{Infobox rocket
|image = Delta II Dawn liftoff 1.jpg
|caption = Sebuah roket Delta II meluncur dari [[Cape Canaveral Air Force Station|Cape Canaveral]] membawa wahana [[Dawn (spacecraft)|Dawn]].
|name = Delta II
|function = [[Launch vehicle]]
|manufacturer = [[United Launch Alliance]]
|country-origin = [[Amerika Serikat]]
|cpl = US$51 million in 1987 (7920-10 model) <ref>{{cite web|url=http://www.spaceflight101.com/delta-ii-7920h-10.html|title=Delta II 7920H-10|access-date=July 1, 2014|url-status=dead |archive-url=https://web.archive.org/web/20140714122955/http://www.spaceflight101.com/delta-ii-7920h-10.html|archive-date=14 July 2014}}</ref> US$137 million in 2018 before retirement <ref>{{cite web |url=https://www.faa.gov/about/office_org/headquarters_offices/ast/media/2018_ast_compendium.pdf|title=The Annual Compendium of Commercial Space Transportation: 2018|date=January 2018|website=Federal Aviation Administration's Office of Commercial Space Transportation|publisher=Bryce Space and Technology}} {{PD-notice}}</ref>
|height = {{cvt|38.2-39|m}}
|diameter = {{cvt|2.44|m}}
|mass = {{cvt|151700-231870|kg}}
|stages = 2 atau 3
|capacities =
{{Infobox rocket/payload
|location = [[Low Earth orbit]]
|kilos = {{cvt|2700-6100|kg}}
}}
{{Infobox rocket/payload
|location = [[Geostationary transfer orbit]]
|kilos = {{cvt|900-2170|kg}}
}}
{{Infobox rocket/payload
|location = [[Heliocentric orbit]]
|kilos = {{cvt|1000|kg}}
}}
|status = Pensiun
|sites = [[Cape Canaveral Air Force Station|Cape Canaveral]], [[Cape Canaveral Space Launch Complex 17|SLC-17]]<br>[[Vandenberg Air Force Base]], [[Vandenberg Space Launch Complex 2|SLC-2W]]
|launches = 156<br>'''Delta 6000:''' 17<br>'''Delta 7000:''' 132<br>'''Delta 7000H:''' 6
|success = 154<br>'''Delta 6000:''' 17<br>'''Delta 7000:''' 130<br>'''Delta 7000H:''' 6
|fail = 1 (Delta 7000)
|partial = 1 (Delta 7000)
|first = {{plainlist|
* '''Delta 6000:''' 14 February 1989 ([[USA-35]])
* '''Delta 7000:''' 26 November 1990 ([[USA-66]])
* '''Delta 7000H:''' 8 July 2003 ([[Opportunity rover]])
}}
|last = {{plainlist|
* '''Delta 6000:''' 24 July 1992 ([[Geotail]])
* '''Delta 7000:''' 15 September 2018 ([[ICESat-2]])
* '''Delta 7000H:''' 10 September 2011 ([[GRAIL]])
}}
{{Infobox rocket/stage
|type = pendorong
|diff = Seri 6000
|name = [[Castor 4A]]
|number = 9
|length = <!--length of a single booster in metres, use {{cvt}}, optional-->
|diameter = <!--diameter of a single booster in metres, use {{cvt}}, optional-->
|empty = <!--empty mass of a single booster/stage in kilograms, use {{cvt}}, optional-->
|gross = <!--gross (fuelled) mass of a single booster/stage, use {{cvt}}, optional-->
|propmass = <!--propellant mass carried by a single booster/stage in kilograms, use {{cvt}}, optional-->
|engines = Solid
|solid = yes
|thrust = {{cvt|478|kN}}
|total = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
|SI = {{cvt|266|isp}}
|burntime = 56 seconds
|propellant = [[Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder]]
}}
{{Infobox rocket/stage
|type = booster
|diff = 7000 Series
|name = [[Graphite-Epoxy Motor|GEM 40]]
|number = 3, 4, or 9
|length = <!--length of a single booster in metres, use {{cvt}}, optional-->
|diameter = <!--diameter of a single booster in metres, use {{cvt}}, optional-->
|empty = <!--empty mass of a single booster in kilograms, use {{cvt}}, optional-->
|gross = <!--gross (fuelled) mass of a single booster, use {{cvt}}, optional-->
|propmass = <!--propellant mass carried by a single booster in kilograms, use {{cvt}}, optional-->
|engines = Solid
|solid = yes
|thrust = {{cvt|492.9|kN}}
|total = <!--total thrust for all boosters in kN, use {{cvt}}, optional-->
|SI = {{cvt|274|isp}}
|burntime = 64 seconds
|propellant = [[Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder]]
}}
{{Infobox rocket/stage
|type = booster
|diff = 7000 Heavy
|name = [[Graphite-Epoxy Motor|GEM 46]]
|number = 9
|length = <!--length of a single booster in metres, use {{cvt}}, optional-->
|diameter = <!--diameter of a single booster in metres, use {{cvt}}, optional-->
|empty = <!--empty mass of a single booster in kilograms, use {{cvt}}, optional-->
|gross = <!--gross (fuelled) mass of a single booster, use {{cvt}}, optional-->
|propmass = <!--propellant mass carried by a single booster in kilograms, use {{cvt}}, optional-->
|engines = Solid
|solid = yes
|thrust = {{cvt|628.3|kN}}
|total = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
|SI = {{cvt|278|isp}}
|burntime = 75 seconds
|propellant = [[Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder]]
}}
{{Infobox rocket/stage
|type = stage
|stageno = First
|name = Thor/Delta XLT(-C)
|length = <!--length of a single stage in metres, use {{cvt}}, optional-->
|diameter = <!--diameter of a single stage in metres, use {{cvt}}, optional-->
|empty = <!--empty mass of a single stage in kilograms, use {{cvt}}, optional-->
|gross = <!--gross (fuelled) mass of a single stage, use {{cvt}}, optional-->
|propmass = <!--propellant mass carried by a single stage in kilograms, use {{cvt}}, optional-->
|engines = 1 [[RS-27]] (6000 series) or [[RS-27A]] (7000 series) <ref>{{cite web|url=http://www.boeing.com/defense-space/space/delta/delta2/delta2.htm|title=Archived copy|access-date=November 3, 2006 |url-status=dead|archive-url=https://web.archive.org/web/20061103194958/http://www.boeing.com/defense-space/space/delta/delta2/delta2.htm|archive-date=November 3, 2006}}</ref>
|thrust = {{cvt|1054|kN}}
|SI = {{cvt|302|isp}}
|burntime = 265 seconds
|fuel = [[RP-1]] / [[LOX]]
}}
{{Infobox rocket/stage
|type = stage
|stageno = Second
|name = [[Delta K]]
|length = <!--length of a single stage in metres, use {{cvt}}, optional-->
|diameter = <!--diameter of a single stage in metres, use {{cvt}}, optional-->
|empty = <!--empty mass of a single stage in kilograms, use {{cvt}}, optional-->
|gross = <!--gross (fuelled) mass of a single stage, use {{cvt}}, optional-->
|propmass = <!--propellant mass carried by a single stage in kilograms, use {{cvt}}, optional-->
|engines = 1 [[AJ-10|AJ10-118K]]
|thrust = {{cvt|43.6|kN}}
|SI = {{cvt|319|isp}}
|burntime = 431 seconds
|fuel = [[Dinitrogen tetroxide|N<sub>2</sub>O<sub>4</sub>]] / [[Aerozine 50]]
}}
{{Infobox rocket/stage
|type = stage
|stageno = Third
|name = [[Payload Assist Module|PAM-D]] (optional)
|length = <!--length of a single stage in metres, use {{cvt}}, optional-->
|diameter = <!--diameter of a single stage in metres, use {{cvt}}, optional-->
|empty = <!--empty mass of a single stage in kilograms, use {{cvt}}, optional-->
|gross = <!--gross (fuelled) mass of a single stage, use {{cvt}}, optional-->
|propmass = <!--propellant mass carried by a single stage in kilograms, use {{cvt}}, optional-->
|engines = [[Star 48B]]
|solid = yes
|thrust = {{cvt|66|kN}}
|SI = {{cvt|286|isp}}
|burntime = 87 seconds
|propellant = Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder
}}
}}
== Referensi ==
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