View source for Engineering:Delta 5000

{{Infobox Rocket
|name = Delta 5000 series
|image = COBELaunch.jpg
|caption = Launch of the Delta 5920 with [[Astronomy:Cosmic Background Explorer|COBE]]
|function = [[Engineering:Expendable launch system|Expendable launch system]]
|country-origin = United States
<!----Costs (optional)---->
|cpl      =  {{US$| 34.22 million}} in 1985 <ref>{{Cite web|url=http://www.astronautix.com/d/delta5000.html|archive-url=https://web.archive.org/web/20160916212108/http://www.astronautix.com/d/delta5000.html|url-status=dead|archive-date=September 16, 2016|title = Delta 5000}}</ref>
|alt-cpl  =  {{US$| 79.99 million}} in 2018
<!----Dimensions (required)---->
|height       =  {{convert|34|m|abbr=on}}
|diameter     =  {{convert|2.44|m|abbr=on}}
|mass         =  {{convert|201,580|kg|abbr=on}}
|stages       =  2
|sites = {{wipe|Vandenberg Air Force Base}} SLC-2W
|launches = 1
|success = 1
|status = Retired
|only = 18 November 1989
<!----Payloads---->
|capacities = 
  {{Infobox rocket/payload
  |location =  [[Astronomy:Low Earth orbit|LEO]]
  |kilos    =  {{convert|3848|kg|abbr=on}}
  }}
  {{Infobox rocket/payload
  |location =  [[Astronomy:Geostationary transfer orbit|GTO]]
  |kilos    =  {{convert|1405|kg|abbr=on}}
  }}
<!----Associated rockets (optional)---->
|family      =  [[Engineering:Delta (rocket family)|Delta]]
|comparable  =  [[Engineering:Delta 4000|Delta 4000]], [[Engineering:Delta II|Delta II]]
<!--Stages/boosters (optional)-->
|stagedata    =  <!--insert one of the following templates for each stage:-->
  {{Infobox rocket/stage
  |type       =  booster
  |diff       =  <!--version stage is used on, if there are multiple variants-->
  |stageno    =  <!--position of stage in rocket, spelled out (eg. First, Second, etc), required-->
  |name       =  Castor 4A
  |number     =  9
  |length     =  {{convert|9.12|m|abbr=on}}
  |diameter   =  {{convert|1.02|m|abbr=on}}
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert}}, optional-->
  |empty      =  {{convert|1,529|kg|abbr=on}}
  |gross      =  {{convert|11,743|kg|abbr=on}}
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert}}, optional--> 
  |engines    =  Solid
  |solid      =  yes
  |thrust     =  {{convert|478.3|kN|abbr=on}}
  |total      =  <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  |SI         =  {{plainlist| <!--specific impulse of an individual booster/stage, in secs, optional-->
** '''Sea level''': 237 seconds 
** '''Vacuum''': 266 seconds
}}
  |burntime   =  56 s
  |propellant =  Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder
  }}
  {{Infobox rocket/stage
  |type       =  stage
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    =  First
  |name       =  Thor/Delta ELT
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  {{convert|22.37|m|abbr=on}}
  |diameter   =  {{convert|2.44|m|abbr=on}}
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert}}, optional-->
  |empty      =  {{convert|4,360|kg|abbr=on}}
  |gross      =  {{convert|84,368|kg|abbr=on}}
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert}}, optional--> 
  |engines    =  1 RS-27
  |solid      =  <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
  |thrust     =  {{convert|1030.2|kN|abbr=on}}
  |total      =  <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  |SI         =  {{plainlist| <!--specific impulse of an individual booster/stage, in secs, optional-->
** '''Sea level''': 262 seconds 
** '''Vacuum''': 296 seconds
}}
  |burntime   =  223 s
  |fuel       =  [[Astronomy:LOX|LOX]] / [[Chemistry:RP-1|RP-1]]
  }}
  {{Infobox rocket/stage
  |type       =  stage
  |diff       =  <!--variant of rocket this is used on, optional-->
  |stageno    =  Second
  |name       =  Delta K
  |number     =  <!--number of boosters, required if type = booster-->
  |length     =  {{convert|5.89|m|abbr=on}}
  |diameter   =  {{convert|2.44|m|abbr=on}}
  |width      =  <!--width of a single booster/stage if not axisymmetric, use {{convert}}, optional-->
  |empty      =  {{convert|950|kg|abbr=on}}
  |gross      =  {{convert|6,954|kg|abbr=on}}
  |propmass   =  <!--propellant mass carried by a single booster/stage in kilograms, use {{convert}}, optional--> 
  |engines    =  1 AJ10-118K
  |solid      =  <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
  |thrust     =  {{convert|43.6|kN|abbr=on}}
  |total      =  <!--total thrust for all boosters in kN, use {{convert}}, optional-->
  |SI         =  319 s
  |burntime   =  431 s
  |fuel       =  {{N2O4}} / [[Chemistry:Aerozine 50|Aerozine 50]]
  }}
}}

The '''Delta 5000 series''' was an American [[Engineering:Expendable launch system|expendable launch system]] which was used to conduct an [[Physics:Orbit|orbit]]al launch in 1989. It was a member of the [[Engineering:Delta (rocket family)|Delta]] family of rockets. Although several variants were put forward, only the Delta 5920 was launched. The designation used a [[Engineering:Delta (rocket family)#Delta numbering system|four digit numerical code]] to store information on the configuration of the rocket. It was built from a combination of spare parts left over from earlier Delta rockets, which were being retired, and parts from the [[Engineering:Delta II|Delta II]] 6000-series, which was just entering service.

The first stage was the RS-27 powered Extended Long Tank Thor, flown on several earlier Delta rockets. Nine Castor-4A [[Engineering:Solid rocket booster|solid rocket booster]]s were attached to increase thrust at lift-off, replacing the less powerful Castor-4 boosters used on the 3000 series. The [[Engineering:Delta-K|Delta-K]] was used as a second stage. In the configuration that was launched, no third stage was flown.

The Delta 5000 was launched just once, from Space Launch Complex 2W at the {{wipe|Vandenberg Air Force Base}}. Launch occurred at 14:34 on 18 November 1989. It was successful, and placed the [[Astronomy:Cosmic Background Explorer|Cosmic Background Explorer]] (COBE) spacecraft into [[Astronomy:Low Earth orbit|low Earth orbit]].<ref>{{Cite web|last=Wade|first=Mark|title=Delta|url=http://www.astronautix.com/lvs/delta.htm|url-status=dead|archive-url=https://web.archive.org/web/20080724064027/http://www.astronautix.com/lvs/delta.htm|archive-date=2008-07-24}}</ref><ref>{{Cite web|last=Krebs|first=Gunter|title=Thor Family|url=https://space.skyrocket.de/doc_lau_fam/thor.htm|url-status=live|access-date=2021-12-21|website=Gunter's Space Page|language=en|archive-url=https://web.archive.org/web/20070806202728/http://space.skyrocket.de:80/doc_lau_fam/thor.htm |archive-date=2007-08-06 }}</ref>

== Payload ==
{{Excerpt|Cosmic Background Explorer}}

==References==
{{Reflist}}

{{Expendable launch systems}}
{{US launch systems}}

[[Category:Delta (rocket family)]]

{{Sourceattribution|Delta 5000}}