MLLV (original) (raw)

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

MLLV

American SSTO VTOVL orbital launch vehicle. Boeing study, 1969, for Saturn follow-on. Plug nozzle, single-stage-to-orbit launch vehicle could itself put 1 million pounds payload into orbit. By addition of up to 12 260 inch solid motors up to 3.5 million pounds payload into orbit with a single launch.

Status: Study 1969. Thrust: 313,624.20 kN (70,505,525 lbf). Gross mass: 25,132,660 kg (55,408,030 lb). Height: 94.00 m (308.00 ft). Diameter: 21.86 m (71.71 ft).

Flyaway Unit Cost 1985$: 1,339.800 million.

Stage Data - MLLV

Stage 0. 12 x 260 inch solid FL. Gross Mass: 1,648,355 kg (3,634,000 lb). Empty Mass: 156,126 kg (344,198 lb). Thrust (vac): 35,391.395 kN (7,956,302 lbf). Isp: 263 sec. Burn time: 114 sec. Isp(sl): 238 sec. Diameter: 6.60 m (21.60 ft). Span: 6.60 m (21.60 ft). Length: 30.48 m (99.99 ft). Propellants: Solid. No Engines: 1. Engine: AJ-260X. Status: Study 1968. Comments: 260 inch solid booster - full length. These would have been the flight configuration motors, replacing the Saturn V first stage or being used as booster motors in various Uprated Saturn and Nova configurations.
Stage 1. 1 x MLLV. Gross Mass: 5,352,400 kg (11,800,000 lb). Empty Mass: 317,400 kg (699,700 lb). Thrust (vac): 71,171.700 kN (16,000,035 lbf). Isp: 455 sec. Burn time: 310 sec. Isp(sl): 367 sec. Diameter: 21.86 m (71.71 ft). Span: 21.86 m (71.71 ft). Length: 78.63 m (257.97 ft). Propellants: Lox/LH2. No Engines: 12. Engine: CD Module. Status: Study 1969. Comments: Boeing study, 1969.

Subtopics

MLLV Core LOx/LH2 propellant rocket stage. Boeing study, 1969.

Family: orbital launch vehicle, SSTO. Country: USA. Engines: CD Module. Stages: AJ-260X, MLLV Core. Agency: Boeing. Bibliography: 267.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z