Comparison Of Continuous Operation And Pulsed Cycles

Adding the PDEs to the results in Figure 4.23, the result is Figure 4.29 that gives the SSTO mass ratio (weight ratio) to reach a 100 nautical mile orbit (185 km) with hydrogen for fuel as a function of the maximum airbreathing Mach number for both continuous and cyclic operation engines. Seven classes of propulsion systems are indicated: rocket-derived, airbreathing (AB) rocket, so-called KLIN cycle, ejector ramjet, scram-LACE, air collection and enrichment systems (ACES) and pulse detonation derived engines (PDR/PDRE). As in Figure 4.23, there is a discontinuity in the results. If the mass ratio to orbit is to be significantly reduced the s.u wMQl s.u wMQl

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