By Terry Kammash

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3/2 = f *o (54) so that its temperature is given by Ta = %E0. The remaining terms that must be inserted into Eqs. (48) and (49) to generate the solution of these equations are the transport terms across the magnetic field between the core and halo regions. If we assume that the particle transport occurs as a result of collisions, then the step size the particle takes is the Larmor radius introduced in Eq. (15) and the frequency is that given by Eq. (32) so that the diffusion coefficients may be written as D = Veipf (55) allowing the particle flux to assume the form tin, r = -D-^ dr Although collisions between unlike particles result in their diffusion magnetic fields, collisions between like particles lead to energy diffusion that case vei in Eq.

84) that P, and A. (n = S w £2. °-65ST n /*2 V = Poyo (1\(1\ s (87) 1 j£jj£| - 1 (88) These results reveal that in the throat the density has dropped to two-thirds its input (reservoir) value, while the pressure has dropped to one-half its value. When these relations are combined and substituted in p - pT, it is clear that the plasma temperature in the throat will also drop relative to its initial value in accordance with ZL - We return now to Eqs. (79) and (80) to calculate the thrust which we can express in terms of the throat or the reservoir parameters; the result is f = I — |A,Po - jA)^ where we recall that A0 is the throat area.

Purchased from American Institute of Aeronautics and Astronautics Chapter 2 High-Performance Fusion Rocket for Manned Space Missions T. Kammash,* M. J. Lee, t and D. L. Galbraith* University of Michigan, Ann Arbor, Michigan 48109 Abstract A high density, mirror-type fusion reactor is proposed as a high-performance propulsion system that would allow manned missions to Mars, or other interplanetary journeys, to be undertaken in relatively short times. Because of the high-temperature plasma confined in this magnetic configuration, which can also serve as a magnetic nozzle, a very large specific impulse (7^) is generated in addition to the large thrust that results from the ejection of the high-density fuel.