MS-IVB
From Wikipedia, the free encyclopedia
The MS-IVB concept rocket stages were to be a development of the highly successful S-IVB rocket stage used on the Saturn V. Had they been created it would have been used on the Saturn MLV and the Saturn V ELV rockets.
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[edit] MS-IVB-1 Specifications
Gross Mass: 120,500 kg(265,600 lb)
Empty Mass: 13,900 kg(30,600 lb)
Thrust(vac): 1,031.600 kN(231,913 lbf)
Isp: 421 sec
Burn Time: 475 sec
Propellants: Lox/LH2
Isp(sl): 200 sec
Diameter: 6.61 m(21.68 ft)
Span: 6.61 m(21.68 ft)
Length: 18.08 m(59.31 ft)
Powerplant: 1x J-2 engine
[edit] MS-IVB-1A Specifications
Gross Mass: 179,200 kg(395,000 lb)
Empty Mass: 20,400 kg(44,900 lb)
Thrust(vac): 1,031.600 kN(231,913 lbf)
Isp: 421 sec
Burn Time: 625 sec
Propellants: Lox/LH2
Isp(sl): 200 sec
Diameter: 6.61 m(21.68 ft)
Span: 6.61 m(21.68 ft)
Length: 22.82 m(74.86 ft)
Powerplant: 1x J-2
[edit] MS-IVB-2 Specifications
Gross Mass: 176,600 kg(389,300 lb)
Empty Mass: 17,800 kg(39,200 lb)
Thrust(vac): 1,401.300 kN(315,025 lbf)
Isp: 447 sec
Burn Time: 489 sec
Propellants: Lox/LH2
Isp(sl): 200 sec
Diameter: 6.61 m(21.68 ft)
Span: 6.61 m(21.68 ft)
Length: 23.12 m(75.85 ft)
Powerplant: 1x J-2
[edit] MS-IVB-3B Specifications
Gross Mass: 179,200 kg(395,000 lb)
Empty Mass: 20,400 kg(44,900 lb)
Thrust(vac): 1,778.900 kN(399,913 lbf)
Isp: 447 sec
Burn Time: 385 sec
Propellants: Lox/LH2
Isp(sl): 200 sec
Diameter: 6.61 m(21.68 ft)
Span: 6.61 m(21.68 ft)
Length: 22.82 m(74.86 ft)
Powerplant: 1x Toroidal 400k
