Delta II: Perbedaan antara revisi
Konten dihapus Konten ditambahkan
k r2.7.2) (Robot: Mengubah pt:Foguete Delta II menjadi pt:Delta II |
k →Pranala luar: clean up |
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| (14 revisi perantara oleh 7 pengguna tidak ditampilkan) | |||
Baris 1:
'''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 (pesawat luar angkasa)|Dawn]].
|name = Delta II
|function = [[Kendaraan peluncur luar angkasa]]
|manufacturer = [[United Launch Alliance]]
|country-origin = [[Amerika Serikat]]
|cpl = 51Juta Dollar AS di tahun 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> 137 juta Dollar AS di tahun 2018 sebelum pensiun <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 = 38.2-39 m (125–128 kaki)
|diameter = 2.44 m (8 kaki 0 inci)
|mass = 151,700–231,870 kg (334,440–511,190 pon)
|stages = 2 atau 3
|capacities =
{{Infobox rocket/payload
|location = [[Orbit Bumi rendah]]
|kilos = {{cvt|2700-6100|kg}}
}}
{{Infobox rocket/payload
|location = [[Orbit transfer geostasioner]]
|kilos = {{cvt|900-2170|kg}}
}}
{{Infobox rocket/payload
|location = [[Orbit heliosentris]]
|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]], [[Kompleks Peluncuran Antariksa 2 Vandenberg|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 Februari 1989 ([[USA-35]])
* '''Delta 7000:''' 26 November 1990 ([[USA-66]])
* '''Delta 7000H:''' 8 Juli 2003 ([[Opportunity|Rover Opportunity]])
}}
|last = {{plainlist|
* '''Delta 6000:''' 24 Juli 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 (tahapan roket)|Castor 4A]]
|number = 9 pendorong
|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 = Padat
|solid = ya
|thrust = 478 kN (107,000 pon<sub>f</sub>)
|total = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
|SI = 266 detik (2.61 km/detik)
|burntime = 56 detik
|propellant = [[Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder]]
}}
{{Infobox rocket/stage
|type = Pendorong
|diff = Seri 7000
|name = [[Graphite-Epoxy Motor|GEM 40]]
|number = 3, 4, atau 9 pendorong
|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 = Padat
|solid = ya
|thrust = 492.9 kN (110,800 pon<sub>f</sub>)
|total = <!--total thrust for all boosters in kN, use {{cvt}}, optional-->
|SI = 274 detik (2.69 km/detik)
|burntime = 64 detik
|propellant = [[Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder]]
}}
{{Infobox rocket/stage
|type = pendorong
|diff = 7000 Heavy
|name = [[Graphite-Epoxy Motor|GEM 46]]
|number = 9 pendorong
|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 = Padat
|solid = ya
|thrust = 628.3 kN (141,200 pon<sub>f</sub>)
|total = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
|SI = 278 detik (2.73 km/detik)
|burntime = 75 detik
|propellant = [[Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder]]
}}
{{Infobox rocket/stage
|type = stage
|stageno = Pertama
|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 = 1,054 kN (237,000 pon<sub>f</sub>)
|SI = 302 detik (2.96 km/detik)
|burntime = 265 detik
|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 = 43.6 kN (9,800 pon<sub>f</sub>)
|SI = 319 detik (3.13 km/detik)
|burntime = 431 detik
|fuel = [[Dinitrogen tetroksida|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 48]]
|solid = yes
|thrust = 66 kN (15,000 ponf)
|SI = 286 detik (2.80 km/detik)
|burntime = 87 detik
|propellant = Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder
}}
}}
== Referensi ==
Baris 12 ⟶ 159:
* [http://kevinforsyth.net/delta/ History of the Delta Launch Vehicle]
* [http://www.cnn.com/TECH/9701/17/rocket.explosion/index.html Article about 1997 failed launch and self-destruction (with video)]
[[Kategori:Boeing]]
[[Kategori:Kendaraan peluncur
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