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The MS-II was a proposed further development of the S-II rocket stage developed by North American Aviation. == Rocket Specifications == Mass: 521,447 kg (1,149,593 lb) Empty Mass: 49,877 kg (109,959 lb) Thrust(vac): 5,165.790 kN (1,161316 lbf) Isp: 425 sec Burn Time: 361 sec Propellants: Lox/LH2. Isp(sl): 306 sec Diameter: 10.06m(33.00ft) Span: 10.06m(33.00ft) Length: 25.88m(84.90ft) Engines: 5x J-2 抄文引用元・出典: フリー百科事典『 ウィキペディア(Wikipedia)』 ■ウィキペディアで「MS-II」の詳細全文を読む スポンサード リンク
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