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
DAC Helios
Part of Bono
Bono DAC Helios.jpg
Bono DAC Helios.jpg
American nuclear-powered orbital launch vehicle. Douglas/Bono 1963 concept for a chemical-boosted / nuclear upper stage launch vehicle, designed as alternatives to the Convair/Ehricke Helios. The baseline version used a nuclear, recoverable upper stage boosted above the atmosphere by a minimum chemical stage.

Status: Study 1963. Payload: 454,500 kg (1,002,000 lb). Thrust: 44,535.70 kN (10,012,024 lbf). Gross mass: 3,275,400 kg (7,221,000 lb). Height: 52.00 m (170.00 ft). Diameter: 24.40 m (80.00 ft). Apogee: 325 km (201 mi).

LEO Payload: 454,500 kg (1,002,000 lb) to a 325 km orbit.

Stage Data - DAC Helios



Subtopics

DAC Helios ISI-1 LOx/LH2 propellant rocket stage. .

DAC Helios ISI-2 Nuclear/LH2 propellant rocket stage. .

DAC Helios-1 LOx/LH2 propellant rocket stage. .

DAC Helios-2 Nuclear/LH2 propellant rocket stage. .

DAC Helios ISI American nuclear-powered orbital launch vehicle. As the basic design, but featuring an Improved Specific Impulse chemical stage that used many engines feeding into single large nozzle.

Family: nuclear-powered, orbital launch vehicle. Country: USA. Engines: Chamber/single nozzle, NERVA 1mlbf. Stages: DAC Helios-1, DAC Helios-2. Agency: Douglas. Bibliography: 214.

Back to top of page
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
© 1997-2019 Mark Wade - Contact
© / Conditions for Use