| Goodyear Project 7969 |
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Goodyear's proposal for the Air Force initial manned space project was a 2.1 m diameter spherical vehicle with a rearward facing tail cone and ablative surface. Flaps were deflected from the cone during re-entry for increased drag and control. The capsule would be launched by an Atlas or a Titan, plus a Vanguard upper stage into a 650 km orbit for a five day mission. Deorbit would be accomplished by a retrorocket providing a 240 m/sec braking impulse. An ablative heat shield was planned. In case of booster failure during ascent to orbit the capsule would be ejected. The spacecraft had a ballistic coefficient (W/CdA) of 250 kg per square meter. Landing precision was within a 1300 km diameter footprint. It was expected that a first manned orbital flight could be achieved 24 months after a go-ahead at a cost of $ 100 million. Design Life: 5 days. Typical orbit: 650 km at 28 deg inclination. Length: 2.13 m (6.98 ft). Maximum Diameter: 2.13 m (6.98 ft). Mass: 900 kg (1,980 lb). Bibliography:
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