Delta II: Perbedaan antara revisi

Konten dihapus Konten ditambahkan
Tidak ada ringkasan suntingan
Tag: Suntingan perangkat seluler Suntingan peramban seluler
Tidak ada ringkasan suntingan
Tag: Suntingan perangkat seluler Suntingan peramban seluler
Baris 60:
|engines = Padat
|solid = ya
|thrust = 478 kN (107,000 ponfpon<sub>f</sub>)
|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 ponfpon<sub>f</sub>)
|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 ponfpon<sub>f</sub>)
|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 = 1,054 kN (237,000 ponfpon<sub>f</sub>)
|SI = 302 detik (2.96 km/detik)
|burntime = 265 detik
Baris 120:
|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-->
Baris 127:
|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 ponfpon<sub>f</sub>)
|SI = 319 detik (3.13 km/detik)
|burntime = 431 detik
|fuel = [[Dinitrogen tetroxidetetroksida|N<sub>2</sub>O<sub>4</sub>]] / [[Aerozine 50]]
}}
{{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 48B48]]
|solid = yes
|thrust = 66 kN (15,000 ponf)