Fusion Energy Space Propulsion by Kammash, Terry Kammash

By Kammash, Terry Kammash

This article offers a set of the unique rules of a few of the prime engineers, scientists, and fusion strength experts. the explicit cause of the gathering is to discover the opportunity of utilizing fusion strength in complex and destiny propulsion platforms in order that appropriate area transportation will be constructed, stronger, and perfected.

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19). 2 ns is shorter than the fuel heating time and also the muon decay time. For the case at hand the fuel is assumed to be instantly ionized upon contact with the H plasma, with an electron heating time rf of about 1 ns which is 5ra. The energy exchange time between the electrons and the fuel ions is, however, typically about 1 ms, making muon catalysis in times of the order of the muon decay time quite feasible. In short, it appears that antimatter assisted fusion in an MICF propulsion system is not beyond the realm of possibility, although further research must be done to firmly establish this approach.

We observe that the left-hand side of Eq. (49) represents the time rate of change of the plasma thermal energy including that which arises from the expansion of the spherical core as represented by dr/d/. The source terms on the right-hand side consist of the energy exchange with the electrons and thermal alphas, the net energy flux arising from the particles that escape the core and those that enter from the halo region, whereas the sink terms reflect energy removal due to participation of fuel ions in the fusion burn, and the bremsstrahlung and synchrotron radiated power as represented by Eqs.

C , where we have employed Eq. (74). throat and reservoir we can write (8D Applying this Bernoulli equation to the £v02+|4 = jv>+|4 (82) which upon assuming that v* « csR in the reservoir, reduces to **'1-'1 <83 > Purchased from American Institute of Aeronautics and Astronautics 30 T. KAMMASH This equation further becomes upon the use of Eq. (78) (84) If we further assume that the pressure at the nozzle exit to be very small, so that we can set cse =? 0, then with the aid of Eq. (81 ), as applied to the exit region, we obtain for the exit velocity ve the result v] = 3c^.

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