Delta II: Perbedaan antara revisi
Konten dihapus Konten ditambahkan
Tidak ada ringkasan suntingan Tag: Suntingan perangkat seluler Suntingan peramban seluler |
k →Pranala luar: clean up |
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Baris 19:
|capacities =
{{Infobox rocket/payload
|location = [[
|kilos = {{cvt|2700-6100|kg}}
}}
{{Infobox rocket/payload
|location = [[Orbit transfer geostasioner
|kilos = {{cvt|900-2170|kg}}
}}
{{Infobox rocket/payload
|location = [[
|kilos = {{cvt|1000|kg}}
}}
Baris 60:
|engines = Padat
|solid = ya
|thrust = 478 kN (107,000
|total = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
|SI = 266 detik (2.61 km/detik)
Baris 78:
|engines = Padat
|solid = ya
|thrust = 492.9 kN (110,800
|total = <!--total thrust for all boosters in kN, use {{cvt}}, optional-->
|SI = 274 detik (2.69 km/detik)
Baris 96:
|engines = Padat
|solid = ya
|thrust = 628.3 kN (141,200
|total = <!--total thrust for all boosters in kN, use {{convert}}, optional-->
|SI = 278 detik (2.73 km/detik)
Baris 112:
|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 =
|SI =
|burntime = 265
|fuel = [[RP-1]] / [[LOX]]
}}
Baris 120:
|type = stage
|stageno = Second
|name = [[Delta
|length = <!--length of a single stage in metres, use {{cvt}}, optional-->
|diameter = <!--diameter of a single stage in metres, use {{cvt}}, optional-->
Baris 127:
|propmass = <!--propellant mass carried by a single stage in kilograms, use {{cvt}}, optional-->
|engines = 1 [[AJ-10|AJ10-118K]]
|thrust =
|SI =
|burntime = 431
|fuel = [[Dinitrogen
}}
{{Infobox rocket/stage
Baris 141:
|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
|solid = yes
|thrust =
|SI =
|burntime = 87
|propellant = Aluminum fuel, ammonium perchlorate oxidizer in an HTPB binder
}}
Baris 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)]
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[[Kategori:Boeing]]
[[Kategori:Kendaraan peluncur
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