Editing Delta II (section)

{{Short description|American space launch system}}
{{about|the rocket|the submarine|Delta-class submarine|the airplane|Fairey Delta 2}}
{{Use American English|date=November 2020}}
{{Use dmy dates|date=August 2019}}
{{Infobox rocket
| logo           = Delta II logo.svg
| logo_upright   = 0.3
| image          = Delta II Dawn liftoff 1.jpg
| caption        = A Delta II rocket launches from [[Cape Canaveral Air Force Station|Cape Canaveral]] carrying the [[Dawn (spacecraft)|Dawn]] spacecraft.

| name           = Delta II
| function       = [[Launch vehicle]]
| manufacturer   = {{Ubli
   | [[McDonnell Douglas]]<br/>(1989–1997)
   | [[Boeing Defense, Space & Security]] (1997–2006)
   | [[United Launch Alliance]] (2006–2018)
}}
| country-origin = [[United States]]

| cpl            = {{Unbulleted list
   | US$51 million in 1987{{efn|(7920-10 model)}}<ref>{{cite web |url=http://www.spaceflight101.com/delta-ii-7920h-10.html |title=Delta II 7920H-10 |access-date=13 August 2024 |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<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 |access-date=13 August 2024 |website=Federal Aviation Administration's Office of Commercial Space Transportation |publisher=Bryce Space and Technology}} {{PD-notice}}</ref>
}}

| height         = {{cvt|38.9|m}}<ref name="data sheet"/>
| diameter       = {{cvt|2.44|m|ft|0}}
| mass           = {{cvt|152000-286100|kg}}<ref name="data sheet"/><ref name ="Guide"/>
| capacities     =

{{Infobox rocket/payload
  | location     = [[Low Earth orbit|LEO]]
  | inclination  = 28.7°
  | kilos        = {{cvt|2776-6107|kg}}<ref name ="Guide">{{cite report |last1=Isakowitz |first1=Steven J. |last2=Hopkins |first2=Joshua B. |last3=Hopkins |first3=Joseph R. Jr. |year=2004 |title=International Reference Guide to Space Launch Systems |publisher=American Institute of Aeronautics and Astronautics |edition=Fourth}}</ref>
}}

{{Infobox rocket/payload
  | location     = [[Geostationary transfer orbit|GTO]]
  | inclination  = 28.7°
  | kilos        = {{cvt|929-2180|kg}}<ref name ="Guide"/>
}}
{{Infobox rocket/payload
  | location     = [[Sun-synchronous orbit|SSO]]
  | inclination  = 98.7°
  | kilos        = {{cvt|1652-3182|kg}}<ref name ="Guide"/>
}}

| status         = Retired
| sites          = {{Unbulleted list
   | [[Cape Canaveral Space Force Station|Cape Canaveral]], [[Cape Canaveral Space Launch Complex 17|SLC-17]]
   | [[Vandenberg Space Force Base|Vandenberg]], [[Vandenberg Space Launch Complex 2|SLC-2W]]
}}
| launches       = {{Unbulleted list
   | 155:
   | {{in5|3}}'''Delta 6000:''' 17
   | {{in5|3}}'''Delta 7000:''' 132
   | {{in5|3}}'''Delta 7000 Heavy:''' 6
}}
| success        = {{Unbulleted list
   | 153:
   | {{in5|3}}'''Delta 6000:''' 17
   | {{in5|3}}'''Delta 7000:''' 130
   | {{in5|3}}'''Delta 7000 Heavy:''' 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 7000 Heavy:''' 7 July 2003 ([[Opportunity rover]])
}}
| last           = {{plainlist|
* '''Delta 6000:''' 24 July 1992 ([[Geotail]])
* '''Delta 7000:''' 15 September 2018 ([[ICESat-2]])
* '''Delta 7000 Heavy:''' 10 September 2011 ([[GRAIL]])
}}

| stagedata      = 
{{Infobox rocket/stage
  | type         = booster
  | diff         = Delta 6000
  | name         = [[Castor 4A]]
  | number       = 9
  | length       = {{cvt|9.2|m}}<ref name="Castor4A"/>
  | diameter     = {{cvt|1.02|m}}
  | empty        = {{cvt|1457|kg}}
  | gross        = {{cvt|11578|kg}}
  | propmass     = <!--propellant mass carried by a single booster in kilograms, use {{cvt}}, optional--> 
  | engines      = Solid
  | solid        = yes
  | thrust       = {{cvt|478.3|kN}}
  | total        = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  | SI           = {{cvt|266|isp}}
  | burntime     = 56 seconds
  | fuel         = [[Hydroxyl-terminated polybutadiene|HTPB]]
}}

{{Infobox rocket/stage
  | type         = booster
  | diff         = Delta 7000
  | name         = [[Graphite-Epoxy Motor|GEM 40]]
  | number       = 3, 4, or 9
  | length       = {{cvt|13.0|m}}<ref name ="Guide"/>
  | diameter     = {{cvt|1.02|m}}
  | empty        = {{cvt|1315|kg}}
  | gross        = {{cvt|13080|kg}}
  | propmass     = <!--propellant mass carried by a single booster in kilograms, use {{cvt}}, optional--> 
  | engines      = Solid
  | solid        = yes
  | thrust       = {{plainlist|
* '''Ground-lit''': {{cvt|499.2|kN}}
* '''Air-lit''': {{cvt|516.2|kN}}
}}
  | total        = <!--total thrust for all boosters in kN, use {{cvt}}, optional-->
  | SI           = {{plainlist|
* '''Ground-lit''': {{cvt|274.0|isp}}
* '''Air-lit''': {{cvt|283.4|isp}}
}}
  | burntime     = 64 seconds
  | fuel         = [[Ammonium perchlorate composite propellant|AP]] / [[Hydroxyl-terminated polybutadiene|HTPB]] / [[Aluminium|Al]]
}}

{{Infobox rocket/stage
  | type         = booster
  | diff         = Delta 7000 Heavy
  | name         = [[Graphite-Epoxy Motor|GEM 46]]
  | number       = 9
  | length       = {{cvt|14.7|m}}<ref name ="Guide"/>
  | diameter     = {{cvt|1.17|m}}
  | empty        = {{cvt|2035|kg}}
  | gross        = {{cvt|19040|kg}}
  | propmass     = <!--propellant mass carried by a single booster in kilograms, use {{cvt}}, optional--> 
  | engines      = Solid
  | solid        = yes
  | thrust       = {{plainlist|
* '''Ground-lit''': {{cvt|608.1|kN}}
* '''Air-lit''': {{cvt|628.5|kN}}
}}
  | total        = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  | SI           = {{plainlist|
* '''Ground-lit''': {{cvt|224.0|isp}}
* '''Air-lit''': {{cvt|284.0|isp}}
}}
  | burntime     = 76 seconds or 178.03 seconds after liftoff
  | fuel         = [[Ammonium perchlorate composite propellant|APCP]] / [[Hydroxyl-terminated polybutadiene|HTPB]] / [[Aluminium|Al]]
}} 
{{Infobox rocket/stage
  | type         = stage
  | stageno      = First
  | name         = Thor/Delta XLT(-C)
  | length       = {{cvt|26.1|m}}<ref name ="Guide"/>
  | diameter     = {{cvt|2.44|m}}
  | empty        = {{cvt|5680|kg}}
  | gross        = {{cvt|101800|kg}}
  | 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=Boeing: Integrated Defense Systems – Delta – Delta II Launch Vehicle Family |access-date=13 August 2024 |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     = 260.5 seconds
  | fuel         = [[RP-1]] / [[LOX]]
}}

{{Infobox rocket/stage
  | type         = stage
  | stageno      = Second
  | name         = [[Delta K]]
  | length       = {{cvt|6|m}}<ref name ="Guide"/>
  | diameter     = {{cvt|2.44|m}}
  | empty        = {{cvt|950|kg}}
  | gross        = {{cvt|6954|kg}}
  | 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      = 1 × [[Star 48B]]
  | solid        = yes
  | thrust       = {{cvt|66|kN}}
  | SI           = {{cvt|286|isp}}
  | burntime     = 87 seconds
  | fuel         = [[Hydroxyl-terminated polybutadiene|HTPB]]  
}}
}}

'''Delta II''' was an [[expendable launch system]], originally designed and built by [[McDonnell Douglas]], and sometimes known as the Thorad Delta 1. Delta II was part of the [[Delta rocket]] family, derived directly from the [[Delta 3000]], and entered service in 1989. There were two main variants, the Delta 6000 and Delta 7000, with the latter also having "Light" and "Heavy" subvariants. During its career, Delta II flew several notable payloads, including 24 [[Global Positioning System]] (GPS) [[GPS satellite blocks|Block II]] satellites, several dozen NASA payloads, and 60 Iridium communication satellites. The rocket flew its final mission, [[ICESat-2]], on 15 September 2018, earning the launch vehicle a streak of 100 successful missions in a row, with the last failure being [[GPS IIR-1]] in 1997.<ref name="data sheet">{{cite web |url=http://www.spacelaunchreport.com/delta2.html |title=Delta II Data Sheet |first=Ed |last=Kyle |website=spacelaunchreport.com |access-date=2014-07-28 |archive-url=https://web.archive.org/web/20140728024436/http://www.spacelaunchreport.com/delta2.html |archive-date=2014-07-28}}</ref> In the late 1990s, Delta II was developed further into the unsuccessful [[Delta III]], which was in turn developed into the more capable and successful [[Delta IV]], though the latter shares little heritage with the original Thor and Delta rockets.