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Rocket vehicles today are limited by the chemical potential of their propellants, regardless of advancements in combustion technology or engine and nozzle material properties. Increasing specific impulse for high thrust levels would widen the spectrum of technically feasible space mission architectures. Current LH2-fueled nuclear thermal engine des...
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... types of MPD accelerators 6,7 are shown in Figure 1. The Linear Hall accelerator tends to be suitable for low-density flows, while the Faraday type accelerator is more efficient for higher density flows. ...
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... load factor, k, is defined as the ratio between electric field applied and the electric field induced by the moving, ionized flow, uB. Because this is a 1D analysis, u refers to flow velocity in the axial x direction, J y is in the transverse y direction, and B is in the mutually perpendicular z direction, as defined in Figure 1. ...
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... best case I sp values were taken for each power input level, forming a Pareto surface. This was done for each chamber temperature condition for different pressure levels, and the results are shown in Figure 10. Corresponding thrusts are plotted in Figure 11. ...
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... was done for each chamber temperature condition for different pressure levels, and the results are shown in Figure 10. Corresponding thrusts are plotted in Figure 11. Because these are best-fit response surfaces, the data was extrapolated to assume I sp values up to 500 s were achievable, although given the MPD accelerator conditions imposed in this study, only I sp values up to 460 s were computed. ...
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... these are best-fit response surfaces, the data was extrapolated to assume I sp values up to 500 s were achievable, although given the MPD accelerator conditions imposed in this study, only I sp values up to 460 s were computed. Observed T comb =3000 K limit Observed T comb =3351 K limit Figure 10. Response surface for the best case I sp values for a given power input. ...
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... this is equivalent to scaling mass flow rate and throat area while maintaining the same expansion ratio and MPD accelerator characteristics. By doing so, the same I sp can be achieved at a lower thrust and power level, rather than decreasing the thrust and power by travelling down the curve in Figure 11. This integration loops until the system has converged on power and propulsion system masses. ...
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... specific power refers only to onboard elements, so if external power sources were present, such as different power beaming techniques, only the collector arrays, wiring, and distribution systems present on the vehicle itself should be included. The resulting conditions for the air-fueled MATR upper stage to meet the Gross, Inert, and Propellant masses of the Centaur 3 upper stage are plotted in Figure 12- Figure 14. Specific powers greater than 4 MW/kg were not included in the plots due to the diminishing returns on system mass. ...
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... specific power refers only to onboard elements, so if external power sources were present, such as different power beaming techniques, only the collector arrays, wiring, and distribution systems present on the vehicle itself should be included. The resulting conditions for the air-fueled MATR upper stage to meet the Gross, Inert, and Propellant masses of the Centaur 3 upper stage are plotted in Figure 12- Figure 14. Specific powers greater than 4 MW/kg were not included in the plots due to the diminishing returns on system mass. ...
