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EEM
American manned spacecraft module. Study 1968. Re-entry at extreme velocities from manned interplanetary missions.

AKA: Earth Entry Module. Status: Study 1968. Gross mass: 7,900 kg (17,400 lb). Height: 5.60 m (18.30 ft). Diameter: 3.20 m (10.40 ft).

The Earth Entry module was a unique biconic design by NASA Langley and Boeing, capable of returning six crew and a metric ton of samples safely to earth from interplanetary missions at re-entry velocities of up to 18 km/sec.

Use of the EEM allowed the mass of propellants for a rocket-powered earth braking maneuver at the end of a planetary mission to be dispensed with, which reduced mission mass substantially. But it was a risky maneuver, and Von Braun's mission profile of a year later returned to rocket braking as allowing more room for error. Mass of the EEM would vary according to the amount of ablative material applied, tailored to individual missions. It would be as high as 7900 kg for returns at 18.3 km/sec from Mars opposition missions, or as low as 6300 kg for returns at 11.6 km/sec from Venus orbiter missions. After burning off between 1100 kg and 2700 kg of ablative heat shield material, the capsule would have slowed to subsonic speed. Parachutes would deploy and flotation bags would cushion the impact of a water landing.

Crew Size: 6. Orbital Storage: 1,100 days.



Family: Manned spacecraft module. Country: USA. Spacecraft: IMIS 1968. Agency: NASA Langley, Boeing. Bibliography: 253.

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