Abstract
A space propulsion system has been proposed which may use the dense plasma focus (DPF) as its source of power.1 Three modes of operation were identified and each was investigated for its usefulness in space travel with special attention paid to a manned Mars mission. Using fusion products to directly produce thrust resulted in Isp's around 106 sec, but produced system thrust-to-weight ratios (F/W) less than 10-5. This F/w is many orders of magnitude less than a typical value of 0.2 for a manned Mars mission which is presently possible with chemical and nuclear thermal rockets.2 Exhausting additional hydrogen propellant over a time period comparable to the flight time results in F/W ratios of 0.003 at Isp's of 10,000 sec. Using large quantities of propellant to burn “impulsively” gave Isp's of 4,000 sec with F/w equal 0.05 for one thruster and 0.132 if 5 thrusters are used.3
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