Astro IV

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Astro IV

American orbital launch vehicle. A two-stage all-LOx/LH2 vehicle proposed for the USAF SLV-4 requirement. Ruled out because it did not use the large segmented solids then favored by the USAF and its think tanks.

Status: Study 1961. Payload: 7,300 kg (16,000 lb). Gross mass: 278,290 kg (613,520 lb). Height: 47.00 m (154.00 ft). Diameter: 5.08 m (16.66 ft). Span: 13.50 m (44.20 ft). Apogee: 480 km (290 mi).

The design apparently used five J-2 engines in the first stage, and a single J-2 in the second stage.

LEO Payload: 7,300 kg (16,000 lb) to a 480 km orbit at 28.00 degrees.

Family: orbital launch vehicle. Country: USA. Spacecraft: Dynasoar. Agency: Convair. Bibliography: 583.

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