NTP design specifications for a broad range of applications

Details NTP design specifications for a broad range of applications NTP design specifications for a broad range of applications

Jun 1993

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993jpmc.confy....b&link_type=abstract

AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 10 p.

Computer Science

Performance

Manned Mars Missions, Nuclear Propulsion, Nuclear Rocket Engines, Planetary Orbits, Propulsion System Performance, Rocket Engine Design, Flight Crews, Nasa Space Programs, Research And Development, Safety Factors

Scientific paper

A study aimed at balancing requirements of the piloted Mars missions based on nuclear thermal propulsion (NTP), taking into account crew safety, cost and scheduale, is presented. It is concluded that a 15 klbf thrust engine is needed for piloted Mars missions and large planetary orbiter scientific missions. Besides, this engine can be used to enhance piloted lunar missions, robotic lunar and Mars missions, resource recovery from comets and asteroids, and increased payloads in earth orbit.

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